[Federal Register Volume 76, Number 47 (Thursday, March 10, 2011)]
[Rules and Regulations]
[Pages 13067-13069]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-5117]



[[Page 13067]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0679; Directorate Identifier 2009-NM-179-AD; 
Amendment 39-16621; AD 2011-05-11]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 
747SP Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. That AD currently requires repetitive 
inspections and torque checks of the hanger fittings and strut forward 
bulkhead of the forward engine mount and adjacent support structure, 
and visual inspections of the internal angle and external bulkhead 
chord and detailed inspection of internal angles, and corrective 
actions if necessary. The existing AD also provides for an optional 
inspection. This new AD requires additional inspections of airplanes 
that have hi-lok bolts and collars at all of the Group B fastener 
locations, except fastener 13, and related investigative and corrective 
actions. This AD also requires repetitive inspections of the internal 
angle, and corrective actions if necessary. This AD also requires, for 
certain airplanes, replacing the fasteners, which terminates certain 
repetitive inspections. This AD was prompted by reports of undertorqued 
or loose fasteners, a cracked bulkhead chord, and a fractured back-up 
angle. We are issuing this AD to detect and correct loose fasteners 
and/or damaged or cracked hanger fittings, back-up angles, and bulkhead 
of the forward engine mount, which could lead to failure of the hanger 
fitting and bulkhead and consequent separation of the engine from the 
airplane.

DATES: This AD is effective April 14, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 14, 
2011.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail [email protected]; 
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.

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 (phone: 800-647-5527) is 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: Ken Paoletti, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6434; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede airworthiness directive (AD) 2007-19-19, amendment 
39-15210 (72 FR 53939, September 21, 2007). That AD applies to the 
specified products. The NPRM was published in the Federal Register on 
July 8, 2010 (75 FR 39185). That NPRM proposed to continue to require 
repetitive inspections and torque checks of the hanger fittings and 
strut forward bulkhead of the forward engine mount and adjacent support 
structure, and visual inspections of the internal angle and external 
bulkhead chord and detailed inspection of internal angles, and 
corrective actions if necessary; and it proposed to retain the optional 
inspection. That NPRM also proposed to require additional inspections 
of airplanes that have hi-lok bolts and collars at all of the Group B 
fastener locations, except fastener 13, and related investigative and 
corrective actions. That NPRM also proposed to require repetitive 
inspections of the internal angle, and corrective actions if necessary; 
and for certain airplanes, replacing the fasteners, which would 
terminate certain repetitive inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Include an Option To Support the Engine

    Boeing requested that we revise paragraph (k) of the NPRM to 
include an option to support the engine while accomplishing the actions 
specified in Boeing Alert Service Bulletin 747-54A2203, Revision 2, 
dated July 9, 2009. Boeing stated that a safe engine support procedure 
is established in Subject 71-00-02 of the Boeing 747 Aircraft 
Maintenance Manual, which contains information for removing and 
installing the power plant using one of two methods: with a crane, 
overhead sling, strut-mounted bootstrap components; or with the PT90-E 
universal engine changer. Boeing stated that using the PT90-E changer 
is optional in the two hoisting procedures. Boeing pointed out that 
Boeing Alert Service Bulletin 747-54A2203, Revision 2, dated July 9, 
2009, clearly states not to use the bootstrap (strut-mounted) 
components method. Boeing stated that all that is required is removing 
the engine weight to remove the engine mount fasteners. Boeing stated 
that doing paragraph (k) of the NPRM would unnecessarily remove the 
engine and cause significant downtime and incur many costs.
    We disagree with the request to include the option to support the 
engine weight. Boeing Alert Service Bulletin 747-54A2203, Revision 2, 
dated July 9, 2009, specifies procedures to remove and install the 
engine. Using other procedures to suspend the engine does not provide a 
satisfactory level of safety. Safety issues may occur when supporting 
the engine weight instead of removing the engine; for example, any 
movement or loads applied to the engine with pneumatic ducts, hydraulic 
lines, and controls connected may cause hidden damage. The engine 
support procedure does not address the weight of the engine to ensure 
that no loads are applied to the strut to allow fastener removal in 
accordance with Boeing Alert Service Bulletin 747-54A2203, Revision 2, 
dated July 9, 2009. In addition, the engine support procedure does not 
require the airplane to be secured to prevent its movement during the 
time that the engine is supported. We have retained the requirement in 
paragraph (k) of this final rule. We have not changed the AD in regard 
to this issue.

[[Page 13068]]

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed.

Costs of Compliance

    There are about 266 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                   Cost per      U.S.-
              Action                Work  hours   labor rate     Parts       airplane    registered   Fleet cost
                                                   per hour                              airplanes
----------------------------------------------------------------------------------------------------------------
Actions (required by AD 2007-19-             40          $85           $0       $3,400          121     $411,400
 19)..............................
Internal Angle Inspection (new               16           85            0        1,360          121      164,560
 action)..........................
Replacement of fasteners (new                24           85            0        2,040          121      246,840
 action)..........................
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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

    We have 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 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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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 airworthiness directive (AD) 
2007-19-19, Amendment 39-15210 (72 FR 53939, September 21, 2007), and 
adding the following new AD:

2011-05-11 The Boeing Company: Amendment 39-16621; Docket No. FAA-
2010-0679; Directorate Identifier 2009-NM-179-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective April 14, 
2011.

Affected ADs

    (b) This AD supersedes AD 2007-19-19, Amendment 39-15210.

Applicability

    (c) This AD applies to The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, 
and 747SP series airplanes, certificated in any category; as 
identified in Boeing Alert Service Bulletin 747-54A2203, Revision 2, 
dated July 9, 2009.

Subject

    (d) Air Transport Association (ATA) of America Code 54: 
Nacelles/Pylons.

Unsafe Condition

    (e) This AD results from the development of a mandating action. 
The Federal Aviation Administration is issuing this AD to detect and 
correct loose fasteners and/or damaged or cracked hanger fittings, 
back-up angles, and bulkhead of the forward engine mount, which 
could lead to failure of the hanger fitting and bulkhead and 
consequent separation of the engine from the airplane.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of a Requirement of AD 2007-19-19, With Updated Service 
Information

Inspections and Related Investigative and Corrective Actions

    (g) Except as provided by paragraphs (i), (l), and (n) of this 
AD: At the applicable compliance times and repeat intervals listed 
in Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-54A2203, Revision 1, dated August 9, 2007, do 
the inspections and applicable related investigative and corrective 
actions in accordance with Parts 2 and 8 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-54A2203, Revision 
1, dated August 9, 2007; or Revision 2, dated July 9, 2009. After 
the effective date of this AD, use only Boeing Alert Service 
Bulletin 747-54A2203, Revision 2, dated July 9, 2009.

New Requirements of This AD

Mandatory Initial and Repetitive Inspections and Related Investigative 
and Corrective Actions

    (h) For all airplanes: Except as provided by paragraph (m) of 
this AD, at the applicable time in Table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-54A2203, 
Revision 2, dated July 9, 2009, do the initial inspection and 
related investigative and corrective actions in accordance with Part 
7 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-54A2203, Revision 2, dated July 9, 2009, except as 
required by paragraphs (k) and (n) of this AD. Repeat the inspection 
thereafter at the applicable time in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 747-54A2203, Revision 2, dated July 
9, 2009.
    (i) For airplanes that were inspected in accordance with in 
Boeing Alert Service

[[Page 13069]]

Bulletin 747-54A2203, dated August 31, 2000; or Revision 1, dated 
August 9, 2007; and that have hi-lok bolts and collars at all of the 
Group B fastener locations: Except as provided by paragraph (m) of 
this AD, at the applicable time in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 747-54A2203, Revision 2, dated July 
9, 2009, do the initial inspection and related investigative and 
corrective actions in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-54A2203, Revision 
2, dated July 9, 2009, except as required by paragraph (n) of this 
AD. Repeat the inspection at the applicable interval in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2203, 
Revision 2, dated July 9, 2009.

Replacement of Hi-Lok Group B Fasteners

    (j) For airplanes that were inspected in accordance with Boeing 
Alert Service Bulletin 747-54A2203, dated August 31, 2000, and that 
have hi-lok bolts and collars at all of the Group B fastener 
locations: Within 18 months after the effective date of this AD, 
replace all hi-lok Group B fasteners in accordance with Part 6 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-54A2203, Revision 2, dated July 9, 2009. Repeat the inspection 
required by Part 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-54A2203, Revision 2, dated July 9, 2009, 
at the applicable interval specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-54A2203, 
Revision 2, dated July 9, 2009.

Exceptions to Service Bulletin

    (k) Where Step 3 of Part 7 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-54A2203, Revision 1, dated August 
9, 2007; or Revision 2, dated July 9, 2009; provides the option to 
support the engine weight instead of removing the engine, this AD 
does not allow that option. This AD requires that the engine be 
removed before performing the inspections required by paragraph (h) 
of this AD.
    (l) Where Boeing Alert Service Bulletin 747-54A2203, Revision 1, 
dated August 9, 2007, specifies a compliance time after the date of 
that service bulletin, this AD requires compliance within the 
specified compliance time after October 9, 2007 (the effective date 
of AD 2007-19-19).
    (m) Where Boeing Alert Service Bulletin 747-54A2203, Revision 2, 
dated July 9, 2009, specifies a compliance time after the date of 
Revision 1 or Revision 2 of that service bulletin, this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (n) Where Boeing Alert Service Bulletin 747-54A2203, Revision 1, 
dated August 9, 2007; or Boeing Alert Service Bulletin 747-54A2203, 
Revision 2, dated July 9, 2009; specifies to contact Boeing for 
appropriate action, this AD requires, before further flight, repair 
of the discrepancy or replacement of the discrepant part using a 
method approved in accordance with the Boeing Commercial Airplanes 
Organization Designation Authorization or in accordance with the 
procedures specified in paragraph (p) of this AD.

Credit for Actions Previously Accomplished in Accordance With Previous 
Service Information

    (o) Actions performed before the effective date of this AD, in 
accordance with Boeing Alert Service Bulletin 747-53A2203, Revision 
1, dated August 9, 2007, are acceptable for compliance with the 
corresponding actions specified in paragraphs (h), (i), and (j) of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Seattle 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: Ken Paoletti, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6434; fax (425) 917-6590. Or, e-mail 
information to [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
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.
    (4) AMOCs approved previously in accordance with AD 2007-19-19, 
Amendment 39-15210, are approved as AMOCs for the corresponding 
provisions of this AD.

Related Information

    (q) For more information about this AD, contact Ken Paoletti, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6434; fax (425) 917-6590.

Material Incorporated by Reference

    (r) You must use Boeing Alert Service Bulletin 747-54A2203, 
Revision 2, dated July 9, 2009, 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, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
[email protected]; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information at the FAA, 
1601 Lind Avenue, SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, 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 February 22, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-5117 Filed 3-9-11; 8:45 am]
BILLING CODE 4910-13-P