[Federal Register Volume 74, Number 134 (Wednesday, July 15, 2009)]
[Rules and Regulations]
[Pages 34225-34229]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-16467]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0138; Directorate Identifier 2008-NM-216-AD;
Amendment 39-15966; AD 2009-15-03]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model BD-700-1A10 and BD-
700-1A11 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
During scheduled maintenance inspection, a bolt which connects
the PCU (power control unit) to the elevator surface was found
fractured in the assembly. Further inspection of the assembly
revealed that the bearing on the PCU rod end had seized, which
resulted in damage to the attachment fitting bushing and fracture of
the bolt. Inspection of other in-service airplanes revealed two more
seized PCU attachment joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of the bolts in both PCUs
on one side could result in disconnection of the elevator control
surface which would lead to flutter and loss of the aircraft.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective August 19, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 19,
2009.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Pong K. Lee, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7324; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on February 23, 2009
(74 FR 8045). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During scheduled maintenance inspection, a bolt which connects
the PCU (power control unit) to the elevator surface was found
fractured in the assembly. Further inspection of the assembly
revealed that the bearing on the PCU rod end had seized, which
resulted in damage to the attachment fitting bushing and fracture of
the bolt. Inspection of other in-service airplanes revealed two more
seized PCU attachment joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of the bolts in both PCUs
on one side could result in disconnection of the elevator control
surface which would lead to flutter and loss of the aircraft.
This Airworthiness Directive (AD) is issued to mandate the
inspection and
[[Page 34226]]
lubrication of all part number (P/N) GT411-3800-5 and GT411-3800-7
PCU attachment joints.
The required actions include inspections for damage and seizure
(including signs of seizure) of the PCU attachment joints, an
inspection for damage (including wear damage, fretting, corrosion,
galling, scoring, fretting wear, and parts that do not meet inspection
requirements) of the PCU attachment joint components, and applicable
corrective actions. You may obtain further information by examining the
MCAI in the AD docket.
Explanation of Revised Service Information
Bombardier has issued the revised service information specified in
the below table. We have changed paragraphs (f)(1) through (f)(5),
paragraph (f)(7), and paragraphs (g)(1) and (g)(2) of this AD to add
the revised service information specified in the following table.
Revised Service Information
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Revision
Service Bulletin level Date
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Bombardier Alert Service Bulletin A700-1A11-27-024 02 November 10, 2008.
Bombardier Alert Service Bulletin A700-27-066..... 02 November 10, 2008.
Bombardier Service Bulletin 700-1A11-27-025....... 01 November 24, 2008.
Bombardier Service Bulletin 700-27-067............ 01 November 24, 2008.
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No additional work is necessary for airplanes on which the
previously issued service information specified in the following table
has been accomplished. We have revised paragraph (f)(6) and added a new
paragraph (g)(3) to this AD to include credit for accomplishing the
actions before the effective date of this AD using the previously
issued service information.
Previously Issued Service Information
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Revision
Service Bulletin level Date
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Bombardier Alert Service Bulletin A700-1A11-27-024 01 October 3, 2008.
Bombardier Alert Service Bulletin A700-27-066..... 01 October 3, 2008.
Bombardier Service Bulletin 700-1A11-27-025....... (\1\) October 9, 2008.
Bombardier Service Bulletin 700-27-067............ (\1\) October 9, 2008.
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\1\ Original.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 157 products of U.S.
registry.
We estimate that it will take about 4 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $80 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $50,240, 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 AD will not have federalism implications
under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify this AD:
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.
[[Page 34227]]
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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 removing Amendment 39-15753 (73 FR
72316, November 28, 2008) and adding the following new AD:
2009-15-03 Bombardier, Inc.: Amendment 39-15966. Docket No. FAA-
2009-0138; Directorate Identifier 2008-NM-216-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
19, 2009.
Affected ADs
(b) This AD supersedes AD 2008-24-12, Amendment 39-15753.
Applicability
(c) This AD applies to Bombardier Model BD-700-1A10 and BD-700-
1A11 airplanes, certificated in any category, serial numbers (S/Ns)
9002 through 9222 inclusive; equipped with elevator power control
units (PCUs) having part number (P/N) GT411-3800-5 or GT411-3800-7.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During scheduled maintenance inspection, a bolt which connects
the PCU (power control unit) to the elevator surface was found
fractured in the assembly. Further inspection of the assembly
revealed that the bearing on the PCU rod end had seized, which
resulted in damage to the attachment fitting bushing and fracture of
the bolt. Inspection of other in-service airplanes revealed two more
seized PCU attachment joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of the bolts in both PCUs
on one side could result in disconnection of the elevator control
surface which would lead to flutter and loss of the aircraft.
This Airworthiness Directive (AD) is issued to mandate the
inspection and lubrication of all part number (P/N) GT411-3800-5 and
GT411-3800-7 PCU attachment joints.
The required actions include inspections for damage and seizure
(including signs of seizure) of the PCU attachment joints, an
inspection for damage (including wear damage, fretting, corrosion,
galling, scoring, fretting wear, and parts that do not meet
inspection requirements) of the PCU attachment joint components, and
applicable corrective actions.
Restatement of Requirements of AD 2008-24-12:
(f) Unless already done: For airplanes on which elevator PCUs
with P/N GT411-3800-5 or P/N GT411-3800-7, S/N 0615 and lower, are
installed, excluding P/N GT411-3800-7 PCUs having a serial number
listed in Table 1 of this AD, and excluding P/N GT411-3800-7 PCUs on
which less than 1,000 flight hours have accumulated on the PCUs as
of December 15, 2008 (the effective date of AD 2008-24-12), do the
actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of this
AD.
Note 1: Units listed in Table 1 of this AD have been lubricated
by the vendor and the inspections required by paragraphs (f)(1),
(f)(2), (f)(3), and (f)(4) of this AD are not required for those
units.
Table 1--Serial Numbers
------------------------------------------------------------------------
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0030 0199
0031 0202
0033 0205
0041 0206
0046 0208
0060 0210
0062 0214
0066 0218
0081 0222
0083 0223
0087 0240
0092 0262
0097 0265
0101 0281
0105 0296
0108 0301
0109 0310
0111 0323
0110 0365
0119 0369
0130 0406
0138 0407
0141 0408
0145 0413
0156 0420
0161 0427
0163 0429
0164 0430
0165 0431
0171 0433
0173 0435
0174 0438
0178 0453
0179 0491
0181 0495
0183 0504
0188 0506
0190 0513
0191 0533
0197 0536
0198 0586
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(1) Within 10 flight cycles or 50 flight hours after December
15, 2008, whichever occurs first: Inspect for damage and wear and
lubricate the PCU attachment joints in accordance with Bombardier
Alert Service Bulletin A700-1A11-27-024, Revision 02, dated November
10, 2008; or Bombardier Alert Service Bulletin A700-27-066, Revision
02, dated November 10, 2008; as applicable.
(2) Within 90 days or 200 flight hours after performing the
actions required by paragraph (f)(1) of this AD, whichever occurs
first: Repeat the inspection and lubrication of the PCU attachment
joints in accordance with Bombardier Alert Service Bulletin A700-
1A11-27-024, Revision 02, dated November 10, 2008; or Bombardier
Alert Service Bulletin A700-27-066, Revision 02, dated November 10,
2008; as applicable.
(3) Within 45 days or 100 flight hours after performing the
actions required by paragraph (f)(2) of this AD, whichever occurs
first: Repeat the inspection and lubrication of the PCU attachment
joints in accordance with Bombardier Alert Service Bulletin A700-
1A11-27-024, Revision 02, dated November 10, 2008; or Bombardier
Alert Service Bulletin A700-27-066, Revision 02, dated November 10,
2008; as applicable. Repeat the inspection thereafter at intervals
not to exceed 45 days or 100 flight hours, whichever occurs first,
until paragraph (f)(4) of this AD is accomplished.
(4) Completion of a disassembly with an inspection for damage,
applicable corrective actions, and lubrication of the PCU attachment
joint components in accordance with Bombardier Service Bulletin 700-
1A11-27-025, Revision 01, dated November 24, 2008; or Bombardier
Service Bulletin 700-27-067, Revision 01, dated November 24, 2008;
as applicable; constitutes terminating action for the inspections
required by paragraphs (f)(1), (f)(2), and (f)(3) of this AD.
(5) Unless already done, if any damage or seizure is found
during any inspection required by paragraphs (f)(1), (f)(2), (f)(3),
and (f)(4) of this AD, before further flight, replace the affected
part in accordance with Bombardier Service Bulletin 700-1A11-27-025,
Revision 01, dated November 24, 2008; or Bombardier Service Bulletin
700-27-067, Revision 01, dated November 24, 2008; as applicable.
[[Page 34228]]
(6) Actions done before December 15, 2008, in accordance with
Bombardier Alert Service Bulletin A700-1A11-27-024 or Bombardier
Alert Service Bulletin A700-27-066, both dated October 2, 2008; or
Revision 01, both dated October 3, 2008; as applicable; are
acceptable for compliance with the corresponding requirements of
this AD.
(7) Unless already done, submit a report to Bombardier of all
findings found during any inspection required by paragraphs (f)(1),
(f)(2), (f)(3), and (f)(4) of this AD, in accordance with the
applicable service bulletin listed in Table 2 of this AD.
(i) If the inspection was done on or after December 15, 2008:
Submit the report within 14 days after the inspection.
(ii) If the inspection was done before December 15, 2008: Submit
the report within 14 days after December 15, 2008.
Table 2--Service Bulletins for Reports
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Revision
Service Bulletin level Date
----------------------------------------------------------------------------------------------------------------
Bombardier Alert Service Bulletin A700-1A11-27-024 02 November 10, 2008.
Bombardier Alert Service Bulletin A700-27-066..... 02 November 10, 2008.
Bombardier Service Bulletin 700-1A11-27-025....... 01 November 24, 2008.
Bombardier Service Bulletin 700-27-067............ 01 November 24, 2008.
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New Requirements of This AD: Actions and Compliance
(g) Unless already done, do the actions specified in paragraph
(g)(1) or (g)(2) of this AD, as applicable, at the time specified.
(1) For airplanes identified in paragraph (f) of this AD: Within
45 days or 100 flight hours after the effective date of this AD,
whichever occurs first, complete a disassembly with an inspection
for damage, applicable corrective actions, and lubrication of the
PCU attachment joint components in accordance with Bombardier
Service Bulletin 700-1A11-27-025, Revision 01, dated November 24,
2008; or Bombardier Service Bulletin 700-27-067, Revision 01, dated
November 24, 2008; as applicable.
(2) For airplanes not identified in paragraph (f) of this AD on
which elevator PCUs with P/N GT411-3800-7 are installed: Within 180
days or 400 flight hours after the effective date of this AD,
whichever occurs first, complete a disassembly with an inspection
for damage, applicable corrective actions, and lubrication of the
PCU attachment joint components in accordance with Bombardier
Service Bulletin 700-1A11-27-025, Revision 01, dated November 24,
2008; or Bombardier Service Bulletin 700-27-067, Revision 01, dated
November 24, 2008; as applicable.
(3) Actions done before the effective date of this AD in
accordance with Bombardier Service Bulletin 700-1A11-27-025, dated
October 9, 2008; or Bombardier Service Bulletin 700-27-067, dated
October 9, 2008; as applicable; are acceptable for compliance with
the corresponding requirements of this AD.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: Paragraph A.3. of the MCAI requires a one-time
inspection; however, since we have changed the compliance time for
the terminating action in paragraph A.4. of the MCAI (refer to
paragraph (g)(1) of this AD), paragraph (f)(3) of this AD requires
repeating the inspections until the terminating action is performed.
Other FAA AD Provisions
(h) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. Send information to Attn: Pong K. Lee, Aerospace
Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York
ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590;
telephone (516) 228-7324; fax (516) 794-5531. Before using any
approved AMOC on any airplane to which the AMOC applies, notify your
principal maintenance inspector (PMI) or principal avionics
inspector (PAI), as appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
(4) Special Flight Permits: As described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), special flight permits are not allowed.
Related Information
(i) Refer to MCAI Canadian Emergency Airworthiness Directive CF-
2008-31, dated October 9, 2008, and the service information
specified in Table 2 of this AD, for related information.
Material Incorporated by Reference
(j) You must use the service information contained in Table 3 of
this AD to do the actions required by this AD, as applicable, unless
the AD specifies otherwise.
Table 3--Material Incorporated by Reference
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Revision
Document level Date
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Bombardier Alert Service Bulletin A700-1A11-27-024 02 November 10, 2008.
Bombardier Alert Service Bulletin A700-27-066..... 02 November 10, 2008.
Bombardier Service Bulletin 700-1A11-27-025....... 01 November 24, 2008.
Bombardier Service Bulletin 700-27-067............ 01 November 24, 2008.
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(1) The Director of the Federal Register approved the
incorporation by reference of the service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; e-mail [email protected]; Internet http://www.bombardier.com.
(3) You may review copies of the 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.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For
[[Page 34229]]
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.
Issued in Renton, Washington, on July 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-16467 Filed 7-14-09; 8:45 am]
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