[Federal Register: August 8, 2003 (Volume 68, Number 153)]
[Rules and Regulations]
[Page 47211-47213]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08au03-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-SW-33-AD; Amendment 39-13255; AD 2003-14-51]
RIN 2120-AA64
Airworthiness Directives; MD Helicopters, Inc., Model MD900
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 2003-14-51, which was sent
previously to all known U.S. owners and operators of the specified MD
Helicopters, Inc. (MDHI) helicopters by individual letters. This AD
requires checking and inspecting each main rotor blade retention bolt
(bolt) and replacing the bolt with an airworthy bolt if necessary. The
actions specified by this AD are intended to prevent failure of a bolt,
loss of main rotor blade, and subsequent loss of control of the
helicopter.
DATES: Effective August 25, 2003, to all persons except those persons
to whom it was made immediately effective by Emergency AD 2003-14-51,
issued on July 2, 2003, which contained the requirements of this
amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 25, 2003.
Comments for inclusion in the Rules Docket must be received on or
before October 7, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2003-SW-33-AD, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137. You may also send comments electronically
to the rules Docket at the following address: 9-asw-adcomments@faa.gov. The service information referenced in this AD may be obtained from
MD Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell
Rd., Mail Stop M615-GO48, Mesa, Arizona 85215-9734, telephone 1-800-
388-3378, fax 480-891-6782, or on the web at http://www.mdhelicopters.com.
This information may be examined at the FAA,
Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas; or at the Office of the Federal Register,
800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aviation Safety Engineer,
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 2960
Paramount Blvd., Lakewood, California 90712, telephone (562) 627-5322,
fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: On June 20, 2003, the FAA issued an
Emergency AD (EAD) 2003-13-51 for the specified MDHI model helicopters
that contained interim actions until certain investigations were
complete. That EAD reuqires certain checks and inspections of bolt,
part number (P/N) 900R3100001-103, replacing the bolt with an airworthy
bolt if necessary. That action was prompted by two instances of failure
of a bolt.
Since the issuance of that EAD, we have new information that
indicates that the pilot check and torque inspection required by the
EAD can be limited to certain bolts. We also determined that
disassembly and a more detailed inspection of the condition of each
bolt is necessary. On July 2, 2003, we superseded EAD 2003-13-51 by
issuing EAD 2003-14-51, which requires certain checks and inspections
of certain bolts and replacing any bolt with an airworthy bolt if
necessary. The EAD also provides terminating action for the
requirements of the EAD.
The FAA has reviewed MD Helicopters Service Bulletin SB900-092R1,
dated June 30, 2003 (SB), which describes procedures for disassembling
and inspecting the bolts.
Since the unsafe condition described is likely to exist or develop
on other MDHI helicopters of the same type design, the FAA issued EAD
2003-14-51 to prevent failure of a bolt, loss of a main rotor blade,
and subsequent loss of control of the helicopter. The AD requires the
following:
[sbull] Before further flight, remove, inspect, and reinstall each
bolt, unless accomplished previously. If segments do not move freely or
a crack is found, replace the bolt with an airworthy bolt before
further flight.
[sbull] Thereafter, until the terminating action is accomplished,
before each start of the engines for each bolt with 400 or more hours
TIS, do a visual check. A pilot may perform the visual check.
[sbull] If a bolt has shifted upward or if there is no gap between
the thrust washer and retainer (the gap indicates that the O ring is
intact), before further flight, inspect the bolt.
[sbull] At specified intervals, until you accomplish the
terminating action, for bolts with 400 or more hours TIS, do a cam
lever force inspection on each bolt, without removing the bolt.
[sbull] Within 30 days, for bolts with 400 or more hours TIS,
disassemble, inspect, and reinstall each airworthy bolt. If a crack,
fretting, or corrosion is found, replace the bolt with an airworthy
bolt before further flight.
[sbull] Before accumulating 400 hours TIS, for each bolt with less
than 400 hours TIS, disassemble, inspect, and reinstall each airworthy
bolt. If a crack, fretting, or corrosion is found, replace the bolt
with an airworthy bolt before further flight.
Doing the required disassembly and inspections of each bolt, P/N
900R3100001-103, constitutes terminating action for the requirements of
this AD. The actions must be accomplished in accordance with the
service bulletin described previously.
An owner/operator (pilot), holding at least a private pilot
certificate, may perform the visual checks required by paragraph (b) of
this AD and must enter compliance into the aircraft maintenance records
in accordance with 14 CFR sections 43.11 and 91.417(a)(2)(v)). A pilot
may perform this check because it is a visual check for a gap or
movement of the bolt and can be performed equally well by a pilot or a
mechanic.
The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
controllability or structural integrity of the helicopter. Therefore,
removing, inspecting, and reinstalling each bolt at the specified time
intervals, and replacing any unairworthy bolt with an airworthy bolt is
required before further flight and this AD must be issued immediately.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on July 2, 2003, to all known U.S. owners and operators of MDHI
Model MD900 helicopters. These conditions still exist, and the AD is
hereby published in the Federal
[[Page 47212]]
Register as an amendment to 14 CFR 39.13 to make it effective to all
persons.
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002) which governs the FAA's AD system. The
regulation now includes material that relates to altered products,
special flight permits, and alternative methods of compliance. Because
we have now included this material in part 39, we no longer need to
include it in each individual AD.
The FAA estimates that this AD will affect 32 helicopters of U.S.
registry, and the inspections and replacement of a bolt will take
approximately 13 work hours per helicopter to accomplish at an average
labor rate of $65 per work hour. Required parts will cost approximately
$800 per bolt (2 bolts per blade and 5 blades) per helicopter. Based on
these figures, we estimate the total cost impact of the AD on U.S.
operators to be $283,040, assuming all bolts are replaced.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available in the Rules Docket for examination by interested persons. A
report that summarizes each FAA-public contact concerned with the
substance of this AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their mailed
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. 2003-SW-33-AD.'' The postcard will be date
stamped and returned to the commenter.
The regulations adopted herein will not have a 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
Reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2003-14-51 MD Helicopters, Inc: Amendment 39-13255. Docket No. 2003-
SW-33-AD. Supersedes Emergency AD 2003-13-51, Docket No. 2003-SW-27-
AD.
Applicability: Model MD900 helicopters, serial number 900-00008
through 900-00114, with main rotor blade retention bolt (bolt), part
number 900R3100001-103, installed, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of a bolt, loss of a main rotor blade, and
subsequent loss of control of the helicopter, accomplish the
following:
(a) Before further flight, remove, inspect, and reinstall the
bolt in accordance with the Accomplishment Instructions, paragraph
2.B., of MD Helicopters Service Bulletin SB900-092 R1, dated June
30, 2003 (SB). If segments do not move freely or a crack is found,
replace the bolt with an airworthy bolt before further flight.
(b) Thereafter, before each start of the engines, for each bolt
with 400 or more hours time-in-service (TIS) or if the hours TIS is
not available for each bolt, visually check each bolt as follows:
(1) Check that the position of each installed bolt has not
shifted upward.
(2) Check for a gap between the thrust washer and retainer.
(3) An owner/operator (pilot), holding at least a private pilot
certificate, may perform the visual check required by this paragraph
and must enter compliance into the aircraft maintenance records in
accordance with 14 CFR sections 43.11 and 91.417(a)(2)(v)).
(c) If a bolt has shifted upward or if there is no gap between
the thrust washer and retainer (the gap indicates that the O ring is
intact), before further flight, inspect the bolt in accordance with
the Accomplishment Instructions, paragraph 2.B., of the SB.
(d) After accomplishing paragraph (a) of this AD, thereafter, at
intervals not to exceed 6 hours TIS, for bolts with 400 or more
hours TIS, do a cam lever force inspection on each bolt, without
removing the bolt, in accordance with the Accomplishment
Instructions, paragraphs 2.B.(3) and 2.B.(6) of the SB.
(e) Within 30 days, for bolts with 400 or more hours TIS,
disassemble, inspect, and reinstall each airworthy bolt in
accordance with the Accomplishment Instructions, paragraph 2.C. of
the SB, except you are not required to report inspection results to
MD Helicopters, Inc. If a crack, fretting, or corrosion is found,
replace the bolt with an airworthy bolt before further flight.
(f) Before accumulating 400 hours TIS, for bolts with less than
400 hours TIS, disassemble, inspect, and reinstall each airworthy
bolt in accordance with the Accomplishment Instructions, paragraph
2.C. of the SB, except you are not required to report inspection
results to MD Helicopters, Inc. If a crack, fretting, or corrosion
is found, replace the bolt with an airworthy bolt before further
flight.
(g) Accomplishing paragraphs (e) or (f) of this AD constitutes
terminating action for all of the requirements of this AD.
(h) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Los Angeles Aircraft Certification Office, FAA, for
information about previously approved alternative methods of
compliance.
(i) The inspections and replacement of a bolt shall be done in
accordance with MD Helicopters Service Bulletin SB900-092 R1, dated
June 30, 2003. This incorporation by reference was approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Copies may be
[[Page 47213]]
obtained from MD Helicopters Inc., Attn: Customer Support Division,
4555 E. McDowell Rd., Mail Stop M615-GO48, Mesa, Arizona 85215-9734,
telephone 1-800-388-3378, fax 480-891-6782, or on the web at http://www.mdhelicopters.com.
Copies may be inspected at the FAA, Office of
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room
663, Fort Worth, Texas; or at the Office of the Federal Register,
800 North Capitol Street, NW., suite 700, Washington, DC.
(j) This amendment becomes effective on August 25, 2003, to all
persons except those persons to whom it was made immediately
effective by Emergency AD 2003-14-51, issued July 2, 2003, which
contained the requirements of this amendment.
Issued in Fort Worth, Texas, on July 29, 2003.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-19976 Filed 8-7-03; 8:45 am]
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