31894 Federal Register / Vol. 74, No. 127 / Monday, July 6, 2009 / Proposed Rules 

Issued in Renton, Washington, on June 25, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–15810 Filed 7–2–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0608; Directorate 

Identifier 2008–NM–215–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 747– 

200C and –200F Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Boeing 747–200C and –200F series 

airplanes. This proposed AD would 

require a high frequency eddy current 

inspection for cracks of certain fastener 

holes, and corrective action if necessary. 

This proposed AD would also require 

repetitive replacements of the upper 

chords, straps (or angles), and radius 

fillers of certain upper deck floor beams, 

and, for any replacement that is done, 

detailed and open-hole HFEC 

inspections for cracks of the modified 

upper deck floor beams, and corrective 

actions if necessary. This proposed AD 

results from a report from the 

manufacturer that the accomplishment 

of certain existing inspections, repairs, 

and modifications is not adequate to 

ensure the structural integrity of the 

affected 7075 series aluminum alloy 

upper deck floor beam upper chords on 

airplanes that have exceeded certain 

thresholds. We are proposing this AD to 

prevent cracking of the upper chords 

and straps (or angles) of the floor beams, 

which could lead to failure of the floor 

beams and consequent loss of 

controllability, rapid decompression, 

and loss of structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by August 20, 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, 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 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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

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–2009–0608; Directorate Identifier 

2008–NM–215–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 

We have received reports that 

operators have found cracks in the 

upper chords and straps (or angles) of 

the upper deck floor beams. The 

airplanes had accumulated between 

16,264 and 23,561 total flight cycles. In 

addition, we received a report from the 

manufacturer that the accomplishment 

of certain existing inspections, repairs, 

and modifications is not adequate to 

ensure the structural integrity of the 

affected 7075 series aluminum alloy 

upper deck floor beam upper chords on 

airplanes that have exceeded certain 

thresholds. Cracks in the upper chords 

or straps (or angles) of an upper deck 

floor beam that are not found and 

repaired could become large and fully 

sever the floor beam. A severed floor 

beam can lead to large deflection or 

deformation of the floor and of the 

adjacent body skin, frames, and 

stringers, and could result in damage 

and unintended inputs to the wire 

bundles and control cables routed 

through the floor beams which could 

affect airplane controllability. If not 

corrected, adjacent severed floor beams 

could result in consequent loss of 

controllability, rapid decompression, 

and loss of structural integrity of the 

airplane. 

Related ADs 

As a result of these reports of cracks, 

Boeing issued Alert Service Bulletin 

747–53A2439, dated July 5, 2001. 

Boeing Alert Service Bulletin 747– 

53A2439 provides procedures for an 

open-hole high frequency eddy current 

(HFEC) or surface HFEC inspection to 

find fatigue cracking in the upper chord 

of the upper deck floor beams, and 

applicable related investigative and 

corrective actions. The actions in Boeing 

Alert Service Bulletin 747–53A2439, 

dated July 5, 2001, are required by AD 

2006–08–02, amendment 39–14556 (71 

FR 18618, April 12, 2006). 

In addition, Boeing has received many 

reports of cracks in the upper chords 

and straps (or angles) of the affected 

floor beams at the fastener locations 

where the upper chords attach to the 

body frames. As a result of these reports 

of cracks, Boeing issued Alert Service 

Bulletin 747–53A2420, dated March 26, 

1998; and Boeing Alert Service Bulletin 

747–53A2429, dated March 22, 2001. 

Boeing Alert Service Bulletin 747– 

53A2420 provides procedures for 

detailed and open-hole HFEC 


cprice-sewell on PROD1PC69 with PROPOSALS
Federal Register / Vol. 74, No. 127 / Monday, July 6, 2009 / Proposed Rules 31895 

inspections of the upper chords of the 

floor beams, and applicable corrective 

actions. Boeing Alert Service Bulletin 

747–53A2429 provides procedures for 

detailed and open-hole HFEC 

inspections and modification of the 

upper chords of the floor beams, and 

applicable corrective actions. The 

actions in Boeing Alert Service Bulletin 

747–53A2420, dated March 26, 1998; 

and Boeing Alert Service Bulletin 747– 

53A2429, dated March 22, 2001, are 

required by AD 2005–07–21, 

amendment 39–14046 (70 FR 18277, 

April 11, 2005). 

To preclude widespread fatigue 

damage, we have determined that we 

should not rely solely on the 

inspections required by AD 2006–08–02 

and AD 2005–07–21 indefinitely. We 

have determined to mandate a 

modification of the floor beams and 

related investigative actions in this 

separate AD action, rather than 

superseding the related ADs. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2696, dated 

October 16, 2008. This service bulletin 

describes procedures for removing the 

upper chords from the upper deck floor 

beams at stations (STA) 340 to 440 

inclusive, 500, and 520, an open-hole 

HFEC inspection for cracks of all the 

fastener holes accessed for upper chord 

removal, and if any cracking is found, 

contacting Boeing for repair 

information, and doing the repair. This 

service bulletin also describes 

procedures for fabricating and installing 

new upper chords and straps (or angles) 

of the upper deck floor beams at STA 

340 to 440 inclusive, 500, and 520 with 

new upper chords, straps (or angles), 

and radius fillers. 

For any airplane on which a 

replacement is done, the service bulletin 

recommends detailed and HFEC 

inspections for cracks of the modified 

upper deck floor beams, and for 

airplanes on which any cracking is 

found, contacting Boeing for repair 

instructions and repairing if necessary. 

For all airplanes, this service bulletin 

specifies to do detailed and HFEC 

inspections for cracks of the upper deck 

floor beams within 15,000 flight cycles 

after the replacement is done, or within 

1,500 flight cycles, whichever occurs 

later. This service bulletin also specifies 

replacing the upper chords and straps 

(or angles) of the upper deck floor 

beams within 6,000 flight cycles after 

doing the detailed and HFEC 

inspections. The service bulletin also 

specifies repetitive detailed and HFEC 

inspections within 15,000 flight cycles 

after the upper chord replacement 

modification. 

Boeing Alert Service Bulletin 747– 

53A2696 refers to Boeing Alert Service 

Bulletin 747–53A2429, Revision 2, 

dated October 16, 2008; and Boeing 

Alert Service Bulletin 747–53A2439, 

Revision 2, dated July 17, 2008; as 

additional sources of information for 

doing the post-modification inspections. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and the Service 

Bulletin.’’ 

Differences Between the Proposed AD 

and the Service Bulletin 

Boeing Alert Service Bulletin 747– 

53A2696, dated October 16, 2008, 

specifies to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by an 

Authorized Representative for the 

Boeing Commercial Airplanes 

Delegation Option Authorization 

Organization whom we have authorized 

to make those findings. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 25 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 

TABLE—ESTIMATED COSTS

Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per product 

Number 

of U.S.- 

registered 

airplanes 

Fleet cost 

663 ........... $80 None ........ $53,040 per inspection/replacement cycle ..... 25 $1,326,000 per inspection/replacement cycle. 

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 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 this 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 


cprice-sewell on PROD1PC69 with PROPOSALS
31896 Federal Register / Vol. 74, No. 127 / Monday, July 6, 2009 / Proposed Rules 

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 adding 

the following new AD: 

Boeing: Docket No. FAA–2009–0608; 

Directorate Identifier 2008–NM–215–AD. 

Comments Due Date 

(a) We must receive comments by August 

20, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

747–200C and –200F series airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a report from the 

manufacturer that the accomplishment of 

certain existing inspections, repairs, and 

modifications is not adequate to ensure the 

structural integrity of the affected 7075 series 

aluminum alloy upper deck floor beam upper 

chords on airplanes that have exceeded 

certain thresholds. We are issuing this AD to 

prevent cracking of the upper chords and 

straps (or angles) of the floor beams, which 

could lead to failure of the floor beams and 

consequent loss of controllability, rapid 

decompression, and loss of structural 

integrity of the airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Initial Inspection and Replacement 

(g) Before the accumulation of 21,000 total 

flight cycles, or within 1,500 flight cycles 

after the effective date of this AD, whichever 

occurs later: Do an open hole high frequency 

eddy current (HFEC) inspection of all the 

fastener holes accessed for upper chord 

removal for cracks, and replace upper chords, 

straps (or angles), and radius fillers of the 

upper deck floor beams, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2696, dated 

October 16, 2008. 

Repetitive Replacements and PostReplacement Inspections 

(h) Within 15,000 flight cycles after doing 

the replacement required by paragraph (g) of 

this AD, or within 1,500 flight cycles after the 

effective date of this AD, whichever occurs 

later: Do detailed and HFEC inspections for 

cracks of the modified upper deck floor 

beams, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2696, dated October 

16, 2008. Within 6,000 flight cycles after 

doing the detailed and HFEC inspections, do 

the replacement specified in paragraph (g) of 

this AD. Repeat the post-replacement 

inspections and replacement at the 

applicable times specified in paragraph 1.E. 

of Boeing Alert Service Bulletin 747– 

53A2696, dated October 16, 2008. 

Repair of Cracks 

(i) If any crack is found during any 

inspection required by this AD: Before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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: Ivan 

Li, Airframe Branch, ANM–120S, FAA, 

Seattle ACO, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6437; fax (425) 917–6590. Or, email 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. 

Issued in Renton, Washington, on June 25, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–15811 Filed 7–2–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0055; Directorate 

Identifier 2008–NM–194–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2–1C, A300 B2–203, A300 B2K– 

3C, A300 B4–103, A300 B4–203, and 

A300 B4–2C Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

NPRM for the products listed above. 

This action revises the earlier NPRM by 

expanding the scope. This proposed 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: 

[T]he FAA has published SFAR 88 (Special 

Federal Aviation Regulation 88). * * * 

Under this regulation, all holders of type 

certificates for passenger transport aircraft 

* * * are required to conduct a design 

review against explosion risks. 

One of the consequences of the Airbus 

design review is the modification of the fuel 

pump wiring to provide protection against 

chafing of the fuel pump cables. This 

condition, if not corrected, could result in 

short circuits leading to fuel pump failure, 

arcing, and possible fuel tank explosion. 

[A previous AD] was issued to require 

* * * modification [of the fuel pump against 

short circuit] * * *. More recently, an 

additional modification of the electrical 

wiring of the outer fuel pump and the 

landing lights on the left (LH) and right (RH) 

sides has been introduced * * *. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by July 31, 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– 


cprice-sewell on PROD1PC69 with PROPOSALS