Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations 13067 

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. 

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 

me.boecom@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. 

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. 


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13068 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations 

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

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Actions (required by AD 2007–19–19) ............................ 40 $85 $0 $3,400 121 $411,400 

Internal Angle Inspection (new action) ............................ 16 85 0 1,360 121 164,560 

Replacement of fasteners (new action) ........................... 24 85 0 2,040 121 246,840 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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 


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Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations 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 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(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 me.boecom@boeing.com; 

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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0150; Directorate 

Identifier 2010–NM–100–AD; Amendment 

39–16619; AD 2011–05–10] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

ATP Airplanes; BAE Systems 

(Operations) Limited Model HS 748 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

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: 

* * * * * 

Recently, during a walk round check, an 

operator found an aileron trim tab hinge pin 

that had migrated sufficiently to cause a 

rubbing foul on the flap. Other reports 

indicate that, for the purposes of expediency, 

it has become common practice during 

maintenance when replacing a control tab, 

instead of unbolting the forward part of the 

piano hinge from the primary control surface, 

the hinge pins are punched out of the hinges. 

Investigations have concluded that, after 

reinserting the pins after maintenance, the 

ends of the hinges may not have been 

pinched, which is likely to have been the 

cause of the detected hinge pin migration. 

This condition [non-pinched hinge pin 

ends], if not detected and corrected, could 

lead to further incidents of migration of a tab 


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