[Federal Register: October 1, 2008 (Volume 73, Number 191)]
[Rules and Regulations]
[Page 56960-56964]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01oc08-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29227; Directorate Identifier 2007-NM-100-AD;
Amendment 39-15664; AD 2008-18-07]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-
300, 747-400, 747-400D, and 747SR series airplanes. For certain
airplanes, this AD requires a material type inspection to determine if
the lower forward corner reveal of the number 3 main entry doors (MEDs)
is a casting. If the reveals are castings, this AD requires repetitive
inspections of the reveals for cracking, and corrective action if
necessary. If the reveals are not castings, this AD requires a detailed
inspection of the reveals for a sharp edge and repetitive inspections
of the reveals for cracking, and corrective action if necessary. For
certain other airplanes, this AD requires only a detailed inspection of
the reveals for a sharp edge and repetitive inspections of the reveals
for cracking, and corrective action if necessary. For certain other
airplanes, this AD requires repetitive inspections of the reveals for
cracking only, and corrective action if necessary. This AD also allows
a certain replacement as an optional action for the material type
inspection for certain airplanes. This AD results from reports of
cracking and/or a sharp edge in the lower forward corner reveal of the
number 3 MEDs. We are issuing this AD to detect and correct fatigue
cracking of the lower forward corner reveal of the number 3 MEDs, which
could lead to the door escape slide departing the airplane when the
door is opened and the slide is deployed, and consequent
[[Page 56961]]
injuries to passengers and crew using the door escape slide during an
emergency evacuation.
DATES: This AD is effective November 5, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 5,
2008.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (NPRM) to
amend 14 CFR part 39 to include an airworthiness directive (AD) that
would apply to certain Boeing Model 747-100, 747-100B, 747-100B SUD,
747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR series
airplanes. That supplemental NPRM was published in the Federal Register
on May 22, 2008 (73 FR 29716). For certain airplanes, that supplemental
NPRM proposed to require a material type inspection to determine if the
lower forward corner reveal of the number 3 main entry doors (MEDs) is
a casting. If the reveals are castings, that supplemental NPRM proposed
to require repetitive inspections of the reveals for cracking, and
corrective action if necessary. If the reveals are not castings, that
supplemental NPRM proposed to require a detailed inspection of the
reveals for a sharp edge and repetitive inspections of the reveals for
cracking, and corrective action if necessary. For certain other
airplanes, that supplemental NPRM proposed to require only a detailed
inspection of the reveals for a sharp edge and repetitive inspections
of the reveals for cracking, and corrective action if necessary. For
certain other airplanes, that supplemental NPRM proposed to require
repetitive inspections of the reveals for cracking only, and corrective
action if necessary. That supplemental NPRM also proposed to allow a
certain replacement as an optional action for the material type
inspection for certain airplanes.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received from the two commenters.
Support for the Supplemental NPRM
Boeing concurs with the supplemental NPRM.
Request To Revise Costs of Compliance
Northwest Airlines (NWA) requests that we revise the Costs of
Compliance section in the supplemental NPRM. NWA points out that Boeing
Special Attention Service Bulletin 747-53-2460, Revision 1, dated
February 13, 2007 (which we referred to in the supplemental NPRM as the
appropriate source of service information for doing the actions)
specifies 11 hours to perform the inspection. NWA also states that it
plans 8 hours to perform the inspection per doorway or 16 hours to
perform the inspection per airplane.
We disagree with the request to revise the Cost of Compliance
section. The 11 hours estimate specified in Boeing Special Attention
Service Bulletin 747-53-2460, Revision 1, includes time to open and
close access. The four-hour estimate specified in this AD represents
the time necessary to perform only the actions actually required by
this AD. We recognize that, in doing the actions required by an AD,
operators might incur incidental costs in addition to the direct costs.
The cost analysis in AD rulemaking actions, however, typically does not
include incidental costs such as the time required to gain access and
close up, time necessary for planning, or time necessitated by other
administrative actions. We have not changed this AD in this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Costs of Compliance
There are about 715 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD.
Estimated Costs
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Number of
Average U.S.-
Action Work hours labor rate Cost per airplane registered Fleet cost
per hour airplanes
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Inspections.......................... 4 $80 $320, per inspection 119 $38,080, per inspection cycle.
cycle.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a
[[Page 56962]]
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979), and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2008-18-07 Boeing: Amendment 39-15664. Docket No. FAA-2007-29227;
Directorate Identifier 2007-NM-100-AD.
Effective Date
(a) This airworthiness directive (AD) is effective November 5,
2008.
Affected ADs
(b) Certain requirements of this AD terminate certain
requirements of AD 2007-12-11, amendment 39-15089.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR
series airplanes, certificated in any category, as identified in
Boeing Special Attention Service Bulletin 747-53-2460, Revision 1,
dated February 13, 2007, except airplanes that have been converted
to an all-cargo configuration. The requirements of this AD also
become applicable at the time when a converted airplane operating in
an all-cargo configuration is converted back to a passenger or
passenger/cargo configuration.
Unsafe Condition
(d) This AD results from reports of cracking and/or a sharp edge
in the lower forward corner reveal of the number 3 main entry doors
(MEDs). We are issuing this AD to detect and correct fatigue
cracking of the lower forward corner reveal of the number 3 MEDs,
which could lead to the door escape slide departing the airplane
when the door is opened and the slide is deployed, and consequent
injuries to passengers and crew using the door escape slide during
an emergency evacuation.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-53-2460, Revision 1, dated February 13, 2007.
Actions for Group 3 Airplanes
(g) For airplanes identified as Group 3 airplanes in the service
bulletin: Before the accumulation of 10,000 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever occurs later, do a detailed inspection for cracking of the
lower forward corner reveals in accordance with Part 8 of the
service bulletin.
(1) If no cracking is found, repeat the inspection thereafter at
intervals not to exceed 6,000 flight cycles until a new or reworked
two-piece reveal is installed in accordance with Part 2 of the
service bulletin. No further action is required by this paragraph
for that location only after the replacement.
Note 1: For the purpose of this AD, a one-piece machined
aluminum reveal may be reworked into a two-piece reveal in
accordance with Part 7 of the service bulletin after it was verified
to be crack free and without a sharp edge in accordance with Part 5
of the service bulletin, or after it was confirmed to be crack free
in accordance with Part 5 of the service bulletin and reworked to
remove a sharp edge in accordance with Part 6 of the service
bulletin.
(2) If cracking is found, do the replacement specified in
paragraph (g)(2)(i) or (g)(2)(ii) of this AD.
(i) Before further flight, replace the reveal with a new or
reworked two-piece reveal in accordance with Part 2 of the service
bulletin. No further action is required by this paragraph for that
location only after the replacement.
(ii) Before further flight, replace the reveal with a new or
reworked one-piece machined aluminum reveal without a sharp edge in
accordance with Part 3 of the service bulletin. Before the
accumulation of 10,000 flight cycles on the replacement reveal since
new, do the inspection for cracking specified in Part 8 of the
service bulletin and repeat the inspection thereafter at intervals
not to exceed 6,000 flight cycles until a new or reworked two-piece
reveal is installed in accordance with Part 2 of the service
bulletin. If any cracking is found during any inspection required by
this paragraph, before further flight, do the action specified in
paragraph (g)(2) of this AD. No further action is required by this
paragraph for that location only after the replacement with a two-
piece reveal.
Note 2: For the purpose of this AD, a one-piece machined
aluminum reveal with a sharp edge may be reworked into a one-piece
machined aluminum reveal without a sharp edge in accordance with
Part 6 of the service bulletin after it is confirmed to be crack
free in accordance with Part 5 of the service bulletin. After the
sharp edge is removed, the one-piece machined aluminum reveal
without a sharp edge may be further reworked into a two-piece reveal
in accordance with Part 7 of the service bulletin.
Actions for Group 2 Airplanes and Group 1, Configuration 2 Airplanes
(h) For airplanes identified as Group 2 airplanes in the service
bulletin: Before the accumulation of 1,500 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever occurs later, do the inspection specified in paragraph (j)
of this AD.
(i) For airplanes identified as Group 1, Configuration 2
airplanes in the service bulletin: Within 1,500 flight cycles after
the lower forward corner reveal was last replaced or 1,000 flight
cycles after the effective date of this AD, whichever occurs later,
do the inspection specified in paragraph (j) of this AD.
(j) At the applicable times specified in paragraphs (h) and (i)
of this AD: Do a detailed inspection of the lower forward corner
reveals for cracking and a sharp edge in accordance with Part 5 of
the service bulletin.
(1) If no cracking and no sharp edge are found, before the
accumulation of 10,000 flight cycles on the lower forward corner
reveal since new, or within 6,000 flight cycles after doing the
inspection required by paragraph (j) of this AD, whichever occurs
later, do the detailed inspection for cracking in accordance with
Part 8 of the service bulletin and inspect thereafter at intervals
not to exceed 6,000 flight cycles, until a new or reworked two-piece
reveal is installed in accordance with Part 2 of the service
bulletin. If any cracking is found during any inspection required by
this paragraph, before further flight, do the action specified in
paragraph (j)(3) of this AD. No further action is required by this
paragraph for that location only after the replacement with a two-
piece reveal.
(2) If no cracking is found but a sharp edge is found, do the
action specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD.
(i) Before further flight, replace the lower forward corner
reveal with a new or reworked two-piece reveal, in accordance with
Part 2 of the service bulletin. No further action is required by
this paragraph for that location only after the replacement.
(ii) Before further flight, replace the reveal with a new or
reworked one-piece machined aluminum reveal without a sharp edge, in
accordance with Part 3 of the service
[[Page 56963]]
bulletin. Before the accumulation of 10,000 flight cycles on the
replacement reveal since new, do the inspection for cracking in
accordance with Part 8 of the service bulletin and inspect
thereafter at intervals not to exceed 6,000 flight cycles, until a
new or reworked two-piece reveal is installed in accordance with
Part 2 of the service bulletin. If any cracking is found during any
inspection required by this paragraph, before further flight, do the
action required by paragraph (j)(3) of this AD. No further action is
required by this paragraph for that location only after the
replacement with a two-piece reveal.
(3) If cracking is found, do the action specified in paragraph
(j)(3)(i) or (j)(3)(ii) of this AD.
(i) Before further flight, replace the reveal with a new or
reworked two-piece reveal, in accordance with Part 2 of the service
bulletin. No further action is required by this paragraph for that
location only after the replacement.
(ii) Before further flight, replace the lower forward corner
reveal with a new or reworked one-piece machined aluminum reveal
without a sharp edge, in accordance with Part 3 of the service
bulletin. Before the accumulation of 10,000 flight cycles on the
replacement reveal since new, do the inspection for cracking in
accordance with Part 8 of the service bulletin and inspect
thereafter at intervals not to exceed 6,000 flight cycles, until a
new or reworked two-piece reveal is installed in accordance with
Part 2 of the service bulletin. If any cracking is found during any
inspection required by this paragraph, before further flight, do the
action required by paragraph (j)(3) of this AD. No further action is
required by this paragraph for that location only after the
replacement with a two-piece reveal.
Actions for Group 1, Configuration 1 Airplanes
(k) For airplanes identified as Group 1, Configuration 1
airplanes in the service bulletin: Before the accumulation of 1,500
total flight cycles, or within 1,000 flight cycles after the
effective date of this AD, whichever occurs later, do a material
type inspection to determine if the lower forward corner reveals are
castings, in accordance with the service bulletin. As an alternative
to the material type inspection, replacing a reveal with a new or
reworked two-piece lower forward corner reveal in accordance with
Part 2 of the service bulletin is terminating action for the
requirements of this paragraph for that location only.
(1) If the forward corner reveal is not a casting: Before
further flight, do the actions specified in paragraph (j) of this AD
except for the inspection for a sharp edge.
(2) If the forward corner reveal is a casting: Before the
accumulation of 7,000 total flight cycles, within 2,000 flight
cycles after the effective date of this AD, or within 3,000 flight
cycles since the forward corner reveal was inspected in accordance
with Boeing Service Bulletin 747-53A2378, whichever is latest, do a
detailed inspection for cracking of the lower forward corner reveal,
in accordance with Part 1 of Boeing Special Attention Service
Bulletin 747-53-2460, Revision 1, dated February 13, 2007.
(i) If no cracking is found: Repeat the inspection specified in
paragraph (k)(2) of this AD thereafter at intervals not to exceed
3,000 flight cycles until a new or reworked two-piece lower forward
corner reveal is installed in accordance with Part 2 of the service
bulletin. No further action is required by this paragraph for that
location only after the replacement.
(ii) If cracking is found: Do the actions specified in paragraph
(k)(2)(ii)(A), (k)(2)(ii)(B), or (k)(2)(ii)(C) of this AD.
(A) Before further flight, weld repair the reveal in accordance
with Part 4 of the service bulletin. Repeat the inspection specified
in paragraph (k)(2) of this AD thereafter at intervals not to exceed
3,000 flight cycles until a new or reworked two-piece reveal is
installed in accordance with Part 2 of the service bulletin. No
further action is required by this paragraph for that location only
after the replacement.
(B) Before further flight, replace the reveal with a new or
reworked two-piece reveal, in accordance with Part 2 of the service
bulletin. No further action is required by this paragraph for that
location only after the replacement.
(C) Before further flight, replace the reveal with a new or
reworked one-piece machined aluminum reveal without a sharp edge, in
accordance with Part 3 of the service bulletin. Before the
accumulation of 10,000 flight cycles on the replacement reveal since
new, do the inspection for cracking in accordance with Part 8 of the
service bulletin and inspect thereafter at intervals not to exceed
6,000 flight cycles, until a new or reworked two-piece reveal is
installed in accordance with Part 2 of the service bulletin. If any
cracking is found during any inspection required by this paragraph,
before further flight, do the action required by paragraph
(k)(2)(ii)(B) or (k)(2)(ii)(C) of this AD. No further action is
required by this paragraph for that location only after the
replacement with a two-piece reveal.
Operator's Equivalent Procedure
(l) Although Step 5 of Figure 8 of the service bulletin
specifies that operators may accomplish the actions in accordance
with ``an operator's equivalent procedure,'' this AD requires
operators to accomplish Step 5 of Figure 8 in accordance with only
the procedures specified in Boeing Standard Overhaul Practices
Manual (SOPM) 20-20-02 as given in the service bulletin. An
``operator's equivalent procedure'' may be used only if approved as
an alternative method of compliance in accordance with paragraph (p)
of this AD.
Compliance With AD 2007-12-11, Amendment 39-15089, for MED 3 Only
(m) Accomplishment of the applicable repair required by this AD
constitutes compliance with the repair of the lower forward corner
casting (reveal) of the number 3 MEDs only, as required by paragraph
(q)(2)(ii) of AD 2007-12-11 (which specifies the actions be done in
accordance with Boeing Service Bulletin 747-53A2378, Revision 1,
dated March 10, 1994; or Boeing Service Bulletin 747-53A2378,
Revision 3, dated August 11, 2005). Accomplishment of the actions of
this AD does not terminate the remaining requirements of AD 2007-12-
11.
Parts Installation
(n) As of the effective date of this AD, no person may install a
door lower forward corner reveal made of cast 356 aluminum on any
airplane at a location specified by this AD.
(o) As of the effective date of this AD, no person may install a
door lower forward corner reveal made of machined 6061 aluminum on
any airplane at a location specified by this AD, unless it has been
confirmed/reworked to be without a sharp edge in accordance with the
service bulletin.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM-120S,
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 917-6437; fax (425)
917-6590; has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
Material Incorporated by Reference
(q) You must use Boeing Special Attention Service Bulletin 747-
53-2460, Revision 1, dated February 13, 2007, to do the actions
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207.
(3) You may review copies of the service information
incorporated by reference at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030, or
go to: http://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.
[[Page 56964]]
Issued in Renton, Washington, on August 20, 2008.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-20091 Filed 9-30-08; 8:45 am]
BILLING CODE 4910-13-P