[Federal Register: January 12, 2009 (Volume 74, Number 7)]
[Proposed Rules]
[Page 1155-1157]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12ja09-11]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1363; Directorate Identifier 2008-NM-104-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-200, -300, and -300F
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 767-200, -300, and -300F series airplanes. This
proposed AD would require repetitive inspections for fatigue cracking
and corrosion of the upper link fuse pin of the nacelle struts, and
related investigative and corrective actions if necessary. This
proposed AD would also provide terminating action for the repetitive
inspections. This proposed AD results from two reports of cracked upper
link fuse pins. We are proposing this AD to prevent fatigue cracking or
corrosion of the upper link fuse pin, which could result in failure of
the fuse pin and consequent reduced structural integrity of the nacelle
strut and possible separation of the strut and engine from the airplane
during flight.
DATES: We must receive comments on this proposed AD by February 26,
2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
[[Page 1156]]
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207;
telephone 206-544-9990; fax 206-766-5682; e-mail DDCS@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221 or
425-227-1152.
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6421; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-1363;
Directorate Identifier 2008-NM-104-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Other Relevant Rulemaking
On September 21, 2000, we issued AD 2000-19-09, amendment 39-11910
(65 FR 58641, October 2, 2000), applicable to certain Boeing Model 767
series airplanes powered by Rolls-Royce RB211 series engines. AD 2000-
19-09 requires modification of the nacelle strut and wing structure,
and addresses fatigue cracking in primary strut structure and
consequent reduced structural integrity of the strut.
On July 29, 2004, we issued AD 2004-16-12, amendment 39-13768 (69
FR 51002, August 17, 2004), applicable to certain Boeing Model 767-200,
-300, and -300F series airplanes powered by Pratt & Whitney engines and
General Electric engines. That AD supersedes three existing
airworthiness directives and requires modification of the nacelle strut
and wing structure. For certain airplanes, that AD also requires
reworking the aft pitch load fitting, and installing a new diagonal
brace fuse pin; for certain other airplanes, that AD requires replacing
the outboard pitch load fitting of the wing front spar with a new,
improved fitting, which terminates certain repetitive inspections. That
AD addresses fatigue cracking in primary strut structure, which could
result in separation of the strut and engine from the airplane.
Discussion
Since we issued AD 2000-19-09 and AD 2004-16-12, we received two
reports of cracked upper link fuse pins. The two airplanes had
accumulated 11,573 total flight cycles and 14,780 total flight cycles
and are powered by Pratt & Whitney PW4000 engines. Boeing analysis
found cracks in the longitudinal direction of the fuse pins. The
longitudinal cracks were the result of fatigue loads. No material
anomalies were found. Fatigue cracking or corrosion of the upper link
fuse pin could result in failure of the fuse pin and consequent reduced
structural integrity of the nacelle strut and possible separation of
the strut and engine from the airplane during flight.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 767-54A0074,
Revision 1, dated April 24, 2008. The service bulletin describes
procedures for repetitive detailed inspections of the upper link fuse
pin of the nacelle struts for corrosion, and related investigative and
corrective actions if necessary. The related investigative and
corrective actions include replacing the fuse pin with a new fuse pin
if corrosion is found; doing a high frequency eddy current (HFEC)
inspection for cracking if no fuse pin corrosion is found; doing a
magnetic particle inspection of the inside surface of the upper link
fuse pin for cracking; and replacing the fuse pin with a new fuse pin
if cracking is found, and applying corrosion preventive compound on the
upper link fuse pin before further flight.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs. This proposed AD would require accomplishing the actions
specified in the service information described previously.
Accomplishing the modifications required by AD 2000-19-09 and AD 2004-
16-12 would terminate the repetitive inspections required by paragraph
(f) of this proposed AD.
Costs of Compliance
We estimate that this proposed AD would affect 354 airplanes of
U.S. registry. We also estimate that it would take about 4 work-hours
per product to comply with this proposed AD. The average labor rate is
$80 per work-hour. Based on these figures, we estimate the cost of this
proposed AD to the U.S. operators to be $113,280, or $320 per product.
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
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a
[[Page 1157]]
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 this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Boeing: Docket No. FAA-2008-1363; Directorate Identifier 2008-NM-
104-AD.
Comments Due Date
(a) We must receive comments by February 26, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767-200, -300, and -300F
series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April
24, 2008.
Unsafe Condition
(d) This AD results from two reports of cracked upper link fuse
pins. We are issuing this AD to prevent fatigue cracking or
corrosion of the upper link fuse pin, which could result in failure
of the fuse pin and consequent reduced structural integrity of the
nacelle strut and possible separation of the strut and engine from
the airplane during flight.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Initial and Repetitive Inspections/Investigative and Corrective Actions
(f) Inspect the upper link fuse pin of the nacelle struts for
fatigue cracking and corrosion at the applicable time specified in
Table 1 of this AD. Do the applicable inspection by doing all the
applicable actions specified in the Accomplishment Instructions of
Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April
24, 2008; and do all applicable related investigative and corrective
actions before further flight. Repeat the applicable inspection at
intervals not to exceed 3,000 flight cycles or 24 months, whichever
is first, until paragraph (g) of this AD has been done.
Table 1--Compliance Times
------------------------------------------------------------------------
At the later of:
Initial
Engine type inspection Grace period
threshold
------------------------------------------------------------------------
JT9D.......................... 14,000 total Within 3,000 flight
flight cycles. cycles or 18 months
after the effective
date of this AD,
whichever is first.
CF6-80A....................... 24,000 total Within 3,000 flight
flight cycles. cycles or 18 months
after the effective
date of this AD,
whichever is first.
PW4000........................ 8,000 total Within 3,000 flight
flight cycles. cycles or 18 months
after the effective
date of this AD,
whichever is first.
CF6-80C2...................... 10,000 total Within 3,000 flight
flight cycles. cycles or 18 months
after the effective
date of this AD,
whichever is first.
RB211......................... 24,000 total Within 3,000 flight
flight cycles. cycles or 18 months
after the effective
date of this AD,
whichever is first.
------------------------------------------------------------------------
Terminating Action in AD 2000-19-09 and AD 2004-16-12
(g) Accomplishment of the modification specified in paragraph
(g)(1) or (g)(2) of this AD, as applicable, terminates the
inspections required by paragraph (f) of this AD.
(1) For Model 767 series airplanes powered by Rolls-Royce RB211
series engines, as identified in AD 2000-19-09: Modification of the
nacelle strut and wing structure, as required by paragraphs (a) and
(b) of AD 2000-19-09.
(2) For Model 767-200, -300, and -300F series airplanes powered
by Pratt & Whitney and General Electric engines, as identified in AD
2004-16-12: Modification of the nacelle strut and wing structure, as
required by paragraphs (a), (b), (d), and (e) of AD 2004-16-12.
Credit for Actions Done Using Previous Service Information
(h) Replacement of the fuse pins with new fuse pins before the
effective date of this AD in accordance with Boeing Service Bulletin
767-54-0074, dated March 27, 1997, is acceptable for compliance with
the corresponding requirements of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Tamara Anderson, Aerospace Engineer, Airframe Branch,
ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6421; 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.
Issued in Renton, Washington, on December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9-313 Filed 1-9-09; 8:45 am]
BILLING CODE 4910-13-P