Document ID: FAA-2009-0865-0004
Agency: faa
Document Type: Rule
Title: 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 Equipped With General Electric CF6-45 or -50 Series Engines, or Equipped With Pratt and Whitney JT9D-3 or -7 (Excluding -70) Series Engines
Posted Date: 2010-01-20T05:00Z

[Federal Register: January 20, 2010 (Volume 75, Number 12)]
[Rules and Regulations]               
[Page 3150-3152]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20ja10-6]                         

[[Page 3150]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0865; Directorate Identifier 2009-NM-023-AD; 
Amendment 39-16168; AD 2010-01-10]
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 Equipped With General Electric CF6-45 or -50 
Series Engines, or Equipped With Pratt & Whitney JT9D-3 or -7 
(Excluding -70) Series Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Model 747-100, 747-100B, 747-100B SUD, 
747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series 
airplanes. That AD currently requires repetitive inspections to detect 
cracks and fractures of the strut front spar chord assembly (including 
the forward side) at each strut location, and repair if necessary. This 
new AD adds a one-time inspection for cracking of the forward side of 
the front spar chord assembly on the inboard and outboard struts, 
installation of a cap skin doubler for certain airplanes, and repair if 
necessary. These actions terminate the repetitive inspections of the 
forward side of the strut front spar chord assembly; the inspections of 
the aft side assembly continue as specified in the existing AD. This AD 
results from a report of a fractured front spar assembly for strut No. 
3, which resulted in the loss of the strut upper link load path. We are 
issuing this AD to detect and correct cracks and fractures of the 
nacelle strut front spar chord assembly. Fracture of the front spar 
chord assembly could lead to loss of the strut upper link load path and 
consequent fracture of the diagonal brace, which could result in in-
flight separation of the strut and engine from the airplane.

DATES: This AD becomes effective February 24, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of February 24, 
2010.
    On January 29, 2007 (72 FR 1427, January 12, 2007), the Director of 
the Federal Register approved the incorporation by reference of a 
certain other publication listed in the AD.

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 me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com.

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: 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

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2007-01-15, amendment 
39-14887 (72 FR 1427, January 12, 2007). The existing AD applies to 
certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. That NPRM 
was published in the Federal Register on September 18, 2009 (74 FR 
47897). That NPRM proposed to continue to require repetitive 
inspections to detect cracks and fractures of the strut front spar 
chord assembly (including the forward side) at each strut location, and 
repair if necessary. That NPRM also proposed to add a one-time 
inspection for cracking of the forward side of the front spar chord 
assembly on the inboard and outboard struts, installation of a cap skin 
doubler for certain airplanes, and repair if necessary. The additional 
actions proposed in that NPRM would terminate the repetitive 
inspections of the forward side of the strut front spar chord assembly; 
the inspections of the aft side assembly would continue as specified in 
the existing AD.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the single comment received 
on the NPRM. Boeing concurs with the proposed requirements specified in 
the NPRM.

Explanation of Changes Made to This AD

    We have revised this AD to identify the legal name of the 
manufacturer as published in the most recent type certificate data 
sheet for the affected airplane models.
    Boeing Commercial Airplanes has received an Organization 
Designation Authorization (ODA), which replaces their previous 
designation as a Delegation Option Authorization holder. We have 
revised paragraph (q)(3) of this AD to delegate the authority to 
approve an alternative method of compliance for any repair required by 
this AD to the Boeing Commercial Airplanes ODA rather than an 
Authorized Representative under the former Delegation Option 
Authorization program.

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been received, and determined that air safety and the 
public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD. 
AD as proposed.

Interim Action

    We consider the actions in this AD to be interim actions for the 
strut front spar chord assembly at each strut location, excluding the 
forward side (the terminating action for the forward side is included 
in this AD). If the manufacturer develops a modification for the 
remainder of the front spar chord assembly, we might consider 
additional rulemaking.

Costs of Compliance

    There are about 411 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.

[[Page 3151]]

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                     Number of U.S.-
              Action                    Work hours        Average labor          Parts           Cost per airplane     registered         Fleet cost
                                                          rate per hour                                                 airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (required by AD        17..................             $80  $0..................  $1,360, per                       85  $115,600, per
 2007[dash]01[dash]15).                                                                         inspection cycle.                     inspection cycle.
One-time inspection and cap skin   30 to 116 \1\.......             $80  $893 to $36,737 \1\.  $3,293 to $46,017                 85  $279,905 to
 doubler installation (new                                                                      \1\.                                  $3,911,445.\1\
 action).
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ Depending on airplane configuration.

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); 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14887 (72 FR 1427, January 12, 2007) and by 
adding the following new airworthiness directive (AD):

2010-01-10 The Boeing Company: Amendment 39-16168. Docket No. FAA-
2009-0865; Directorate Identifier 2009-NM-023-AD.

Effective Date

    (a) This AD becomes effective February 24, 2010.

Affected ADs

    (b) This AD supersedes AD 2007-01-15, Amendment 39-14887.

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, equipped 
with General Electric CF6-45 or -50 series engines, or equipped with 
Pratt & Whitney JT9D-3 or -7 (excluding -70) series engines, as 
identified in Boeing Alert Service Bulletin 747-54A2224, Revision 1, 
dated November 16, 2006.

Subject

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

Unsafe Condition

    (e) This AD results from a report of a fractured front spar 
assembly for strut No. 3, which resulted in the loss of the strut 
upper link load path. The Federal Aviation Administration is issuing 
this AD to detect and correct cracks and fractures of the nacelle 
strut front spar chord assembly. Fracture of the front spar chord 
assembly could lead to loss of the strut upper link load path and 
consequent fracture of the diagonal brace, which could result in in-
flight separation of the strut and 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 Requirements of AD 2004-25-05, Amendment 39-13893

Aft Side Detailed and High Frequency Eddy Current (HFEC) Inspections 
With New Service Information

    (g) Within 90 days after December 27, 2004 (the effective date 
of AD 2004-25-05, which was superseded by AD 2007-01-15), perform 
detailed and HFEC inspections to detect any cracks or fractures of 
the front spar chord assembly for strut numbers 1 through 4 
inclusive, in accordance with Boeing Alert Service Bulletin 747-
54A2224, dated September 30, 2004; or in accordance with Part 1--Aft 
Side Inspection of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-54A2224, Revision 1, dated November 16, 2006. 
As of January 29, 2007 (the effective date of AD 2007-01-15), only 
Part 1--Aft Side Inspection of the Accomplishment Instructions of 
Revision 1 of Boeing Alert Service Bulletin 747-54A2224, Revision 1, 
dated November 16, 2006, may be used.
    (h) Accomplishment of the detailed and HFEC inspections in 
accordance with Boeing 747 Fleet Team Digest 747-FTD-54-04002, dated 
April 15, 2004, May 4, 2004, June 1, 2004, July 12, 2004, or July 
28, 2004; or Boeing Message 1-C6ELC (Service Request ID No.: 
218724992), dated April 14, 2004; before December 27, 2004, is 
considered acceptable for compliance with the requirements of 
paragraph (g) of this AD.

Repetitive Inspections

    (i) For airplanes on which no crack or fracture is detected 
during the inspections

[[Page 3152]]

required by paragraph (g) of this AD: At the applicable times 
specified in Table 1--Repetitive Intervals of this AD, repeat the 
detailed and HFEC inspections required by paragraph (g) of this AD.

                                          Table 1--Repetitive Intervals
----------------------------------------------------------------------------------------------------------------
 For airplanes identified in Boeing
       Alert Service Bulletin
 747[dash]54A2224, dated September               Repeat the inspections at intervals not to exceed--
   30, 2004; or Revision 1, dated
      November 16, 2006; as--
----------------------------------------------------------------------------------------------------------------
Group 1............................  1,000 flight cycles or 18 months, whichever occurs first.
Group 2 and Group 3................  1,200 flight cycles or 18 months, whichever occurs first.
Group 4 and Group 6................  1,500 flight cycles or 18 months, whichever occurs first.
Group 5............................  2,000 flight cycles or 18 months, whichever occurs first.
----------------------------------------------------------------------------------------------------------------

Corrective Action

    (j) If any crack or fracture is found during any inspection 
required by paragraphs (g) and (i) of this AD, and Boeing Alert 
Service Bulletin 747-54A2224, dated September 30, 2004; or Revision 
1, dated November 16, 2006; specifies contacting Boeing for 
appropriate action: Before further flight, repair the crack or 
fracture using a method approved in accordance with the procedures 
specified in paragraph (q) of this AD.

Restatement of Requirements of AD 2007-01-15

Forward Side Detailed and HFEC Inspections

    (k) Within 90 days after January 29, 2007 the effective date of 
AD 2007-01-15), do detailed and HFEC inspections for any cracks or 
fracture of the front spar chord assembly for strut numbers 1, 2, 3, 
and 4, in accordance with Part 2--Forward Side Inspection of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2224, Revision 1, dated November 16, 2006. If no crack or 
fracture is found, repeat the inspections thereafter at the 
applicable interval specified in Table 1 of this AD. Doing the 
inspections required by paragraph (n) of this AD terminates the 
forward side detailed and HFEC inspection requirements of this 
paragraph.

Corrective Action for Forward Side Inspection

    (l) If any crack or fracture is found during any inspection 
required by paragraph (k) of this AD, and Boeing Alert Service 
Bulletin 747-54A2224, Revision 1, dated November 16, 2006, specifies 
to contact Boeing for appropriate action: Before further flight, 
repair the crack or fracture using a method approved in accordance 
with the procedures specified in paragraph (q) of this AD.

Credit for Inspections Done According to Boeing 747 Fleet Team Digest

    (m) Detailed and HFEC inspections done before January 29, 2007, 
in accordance with Boeing 747 Fleet Team Digest 747-FTD-54-06002, 
dated June 29, 2006; or October 16, 2006; are acceptable for 
compliance with the initial inspection required by paragraph (k) of 
this AD.

New Requirements of This AD

Inspection and Corrective Actions

    (n) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-54A2230, dated 
October 30, 2008; except that where the service bulletin specifies a 
compliance time after the date on the service bulletin, this AD 
requires compliance within the specified compliance time after the 
effective date of this AD: Do an open-hole high frequency eddy 
current (HFEC) inspection for cracking of the forward side of the 
front spar chord assembly on the inboard and outboard struts; and, 
for airplanes on which the cap skin doubler is not installed, 
install the cap skin doubler; in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-54A2230, dated 
October 30, 2008.
    (o) If any crack is found during the inspection required by 
paragraph (n) of this AD: Before further flight, repair the crack 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (p) Doing all applicable actions required by paragraphs (n) and 
(o) of this AD terminates the repetitive forward side detailed and 
HFEC inspection requirements of paragraph (k) of this AD. All aft 
side inspection requirements of this AD remain in effect.

Alternative Methods of Compliance (AMOCs)

    (q)(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 Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6434; fax (425) 
917-6590. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-
Requests@faa.gov.
    (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 principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (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 
(ODA) that 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 2007-01-15 
are approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

    (r) You must use Boeing Alert Service Bulletin 747-54A2224, 
Revision 1, dated November 16, 2006; and Boeing Alert Service 
Bulletin 747-54A2230, dated October 30, 2008; as applicable; 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 Boeing Alert Service Bulletin 747-
54A2230, dated October 30, 2008, under 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Boeing Alert Service Bulletin 747-
54A2224, Revision 1, dated November 16, 2006, on January 29, 2007 
(72 FR 1427, January 12, 2007).
    (3) 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 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
    (4) 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.
    (5) 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 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 December 30, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-31363 Filed 1-19-10; 8:45 am]
BILLING CODE 4910-13-P