47900 Federal Register / Vol. 74, No. 180 / Friday, September 18, 2009 / Proposed Rules 

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 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-ACOAMOC-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 an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization 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 2007–01–15, are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Issued in Renton, Washington, on 

September 11, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–22577 Filed 9–17–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0866; Directorate 

Identifier 2009–NM–074–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model MD–11 and MD–11F 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

McDonnell Douglas Model MD–11 and 

MD–11F airplanes. The existing AD 

currently requires a one-time inspection 

to determine if metallic transitions are 

installed on wire harnesses of the tail 

tank fuel transfer pumps, and to 

determine if damaged wires are present; 

and repair, if necessary. This proposed 

AD would require modifying the case 

grounding for the alternate fuel pump of 

the tail tank, the leak detection thermal 

switch grounding for the number 2 

engine, and wire braid grounding in the 

empennage and number 2 engine inlet. 

This proposed AD would also remove 

one airplane from the applicability of 

the existing AD. This proposed AD 

results from reports that the wire 

assembly for the alternate fuel pump is 

missing a case ground wire, and the 

lightning protection wire braid for wire 

assemblies located in the empennage 

and number 2 engine inlet are grounded 

improperly. We are proposing this AD 

to prevent insufficient grounding of the 

fuel pump, which in combination with 

an electrical failure within the fuel 

pump and a compromised electrical 

bond could cause a fuel tank ignition, 

resulting in consequent fire or 

explosion. 

DATES: We must receive comments on 

this proposed AD by November 2, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.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 or 425–227–1152. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 


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Federal Register / Vol. 74, No. 180 / Friday, September 18, 2009 / Proposed Rules 47901 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5262; fax (562) 

627–5210. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0866; Directorate Identifier 

2009–NM–074–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On December 2, 1999, we issued AD 

99–25–14, amendment 39–11457 (64 FR 

69389, December 13, 1999), for certain 

McDonnell Douglas Model MD–11 and 

MD–11F airplanes. That AD requires a 

one-time inspection to determine if 

metallic transitions are installed on wire 

harnesses of the tail tank fuel transfer 

pumps, and to determine if damaged 

wires are present; and repair, if 

necessary. That AD also requires 

repetitive inspections of the repaired 

area; and a permanent modification of 

the wire harnesses if metallic transitions 

are not installed, which terminates the 

repetitive inspections. That AD resulted 

from a report of chafing and damage to 

a wire harness of a tail tank fuel transfer 

pump. We issued that AD to prevent 

wire chafing and damage, which could 

result in an inoperative fuel transfer 

pump and/or an increased risk of a fire 

or explosion from a fuel leak. 

Actions Since Existing AD Was Issued 

Since we issued AD 99–25–14, we 

have received reports that the wire 

assembly for the alternate fuel pump is 

missing a case ground wire, and the 

lightning protection wire braid for wire 

assemblies located in the empennage 

and number 2 engine inlet are grounded 

improperly. Further investigation 

revealed that the wiring of the anti-ice 

leak detection thermal switch of the 

number 2 engine was not included in 

the wire assembly, and that the support 

bracket of the leak detection thermal 

switch was not electrically bonded to 

the engine spar of the number 2 engine. 

Insufficient grounding of the fuel pump, 

in combination with an electrical failure 

within the fuel pump and a 

compromised electrical bond, could 

cause a fuel tank ignition, resulting in 

consequent fire or explosion. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin MD11–28A140, dated 

November 6, 2008. The service bulletin 

describes procedures to modify the case 

grounding for the alternate fuel pump of 

the tail tank and the leak detection 

thermal switch grounding for the 

number 2 engine. The modification also 

includes modifying the wire metal braid 

grounding in the empennage and the 

inlet of the number 2 engine, and testing 

the leak detection thermal switch for 

correct operation. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 99–25– 

14 and would retain the requirements of 

the existing AD. This proposed AD 

would also require accomplishing the 

actions specified in the ‘‘Relevant 

Service Information’’ described 

previously. 

Changes to Existing AD 

This proposed AD would retain all 

requirements of AD 99–25–14. Since AD 

99–25–14 was issued, the AD format has 

been revised, and certain paragraphs 

have been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

99–25–14 

Corresponding 

requirement in this 

proposed AD 

Paragraph (a) ............ paragraph (g). 

In addition, we have revised the 

applicability of AD 99–25–14 by 

referring to Boeing Alert Service 

Bulletin MD11–28A140, dated 

November 6, 2008, in paragraph (c) of 

this AD. This proposed AD would 

remove one airplane, fuselage number 

450, from the applicability due to hull 

loss. 

Costs of Compliance 

There are about 13 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection (required by AD 

99–25–14).

1 $80 $80 $80, per inspection 

cycle.

9 $720, per inspection cycle. 

Modification (new proposed 

action).

16 80 1,248 $2,528 .................... 9 $22,752. 

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 


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47902 Federal Register / Vol. 74, No. 180 / Friday, September 18, 2009 / Proposed Rules 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 amendment 39–11457 (64 FR 

69389, December 13, 1999) and adding 

the following new AD: 

McDonnell Douglas: Docket No. FAA–2009– 

0866; Directorate Identifier 2009–NM– 

074–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by November 2, 2009. 

Affected ADs 

(b) This AD supersedes AD 99–25–14. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Model MD–11 and MD–11F airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin MD11–28A140, 

dated November 6, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from reports that the 

wire assembly for the alternate fuel pump is 

missing a case ground wire, and the lightning 

protection wire braid for wire assemblies 

located in the empennage and number 2 

engine inlet are grounded improperly. The 

Federal Aviation Administration is issuing 

this AD to prevent insufficient grounding of 

the fuel pump, which in combination with an 

electrical failure within the fuel pump and a 

compromised electrical bond could cause a 

fuel tank ignition, resulting in consequent 

fire or explosion. 

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 99–25– 

14 With No Changes 

Inspection and Corrective Actions 

(g) Within 30 days after January 18, 2000 

(the effective date of AD 99–25–14), perform 

a one-time visual inspection of the wire 

harnesses of the tail tank fuel transfer pumps 

to determine if metallic transitions are 

installed, and to determine if damaged wires 

are present, in accordance with McDonnell 

Douglas Alert Service Bulletin MD11– 

28A101, dated August 24, 1998 (‘‘the service 

bulletin’’). 

(1) If all metallic transitions are installed, 

no further action is required by paragraph (g) 

of this AD. 

(2) If metallic transitions are not installed, 

accomplish the following: 

(i) Prior to further flight, accomplish the 

temporary repair in accordance with 

condition 2 of the service bulletin; 

(ii) Repeat the visual inspection thereafter 

at intervals not to exceed 2 years; and 

(iii) Within 5 years after January 18, 2000, 

permanently modify the wire harnesses in 

accordance with McDonnell Douglas Service 

Bulletin MD11–28–102, Revision 01, dated 

June 23, 1999. Accomplishment of this 

modification constitutes terminating action 

for the repetitive inspection requirements of 

this AD. 

Note 1: Modification of the wire harnesses 

accomplished prior to January 18, 2000 (the 

effective date of AD 99–25–14), in 

accordance with McDonnell Douglas Service 

Bulletin MD11–28–102, dated January 29, 

1999, is considered acceptable for 

compliance with the modification required 

by paragraph (g)(2)(iii) of this AD. 

New Requirements of This AD 

Modification 

(h) Within 72 months after the effective 

date of this AD, modify the case grounding 

for the alternate fuel pump of the tail tank, 

the leak detection thermal switch grounding 

for the number 2 engine, and wire braid 

grounding in the empennage and number 2 

engine inlet, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD11–28A140, dated 

November 6, 2008. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Los Angeles 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: 

Samuel Lee, Aerospace Engineer, Propulsion 

Branch, ANM–140L, FAA, Los Angeles ACO, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 627– 

5262; fax (562) 627–5210. 

(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. 

Issued in Renton, Washington, on 

September 11, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–22580 Filed 9–17–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Office of the Secretary 

14 CFR Part 382 

[Docket No. OST–2009–0093] 

Nondiscrimination on the Basis of 

Disability in Air Travel 

AGENCY: Office of the Secretary (OST), 

DOT. 

ACTION: Request for comments on 

petition for rulemaking. 

SUMMARY: An advocacy group 

representing users of psychiatric service 

dogs has petitioned the Department to 

eliminate a provision of the Department 

of Transportation’s Air Carrier Access 

regulation. The provision in question 

permits air carriers to require 

documentation and 48 hours’ advance 

notice for users of psychiatric service 

animals. In this document, the 

Department is seeking comment on the 

group’s petition and related questions. 

This document is not a notice of 

proposed rulemaking. The Department 

has not decided whether to grant the 

petition by initiating rulemaking action 

or to deny the petition and retain the 

provisions without change. The 

Department will publish a document in 


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