Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations 49805 

2009–20–04 Glaser-Dirks Flugzeugbau 

Gmbh: Amendment 39–16027; Docket 

No. FAA–2009–0881; Directorate 

Identifier 2009–CE–050–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 19, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model DG–100 

gliders, serial numbers 5 and 21 through 103, 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

The Elevator control bearing stand RU19 

was required to be inspected for correct 

production in 1978 in accordance with 

Technical Note (TN) No. 301/6. In 2009, an 

accident occurred with a DG–100. The 

suspension bolt was found torn out of the 

bearing stand making the elevator 

uncontrollable. The investigation confirmed 

that the bearing stand had not been produced 

correctly. It is therefore assumed that the 

inspections per TN 301/6 did not produce 

reliable results. 

As a consequence, this new Airworthiness 

Directive (AD) mandates replacement of the 

bearing stand with a reinforced version. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Before further flight after October 19, 

2009 (the effective date of this AD), inspect 

the bearing stand RU19 following paragraph 

1 of the Instructions section of DG 

Flugzeugbau Technical note No. 301/26, Rev. 

1, dated August 4, 2009. You may take credit 

for this paragraph if the bearing stand was 

inspected before October 19, 2009 (the 

effective date of this AD) following DG 

Flugzeugbau Technical note No. 301/26, 

dated July 16, 2009. 

(2) If any discrepancy is found (crack, 

delamination, etc.), before further flight 

replace the bearing stand RU19 following 

paragraph 3 of the Instructions section of DG 

Flugzeugbau Technical note No. 301/26, Rev. 

1, dated August 4, 2009. 

(3) Within 3 months after October 19, 2009 

(the effective date of this AD) replace the 

bearing stand RU19 following paragraph 3 of 

the Instructions section of DG Flugzeugbau 

Technical note No. 301/26, Rev. 1, dated 

August 4, 2009. You may take credit for this 

paragraph if the bearing stand RU19 has been 

replaced before October 19, 2009 (the 

effective date of this AD) following DG 

Flugzeugbau Technical note No. 301/6, dated 

May 29, 1978, or following paragraph 3 of the 

Instructions section of DG Flugzeugbau 

Technical note No. 301/26, dated July 16, 

2009. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: 

(1) DG Flugzeugbau GmbH Technical Note 

No. 301/26, Rev. 1, dated August 4, 2009, 

states that instruction 1 may be executed by 

the pilot/owner. By FAA regulations, this AD 

requires all affected gliders to have the 

required actions done by an appropriately 

rated mechanic. 

(2) The MCAI states to do the actions 

following DG Flugzeugbau GmbH Technical 

Note No. 301/26, dated July 16, 2009. DG 

Flugzeugbau GmbH updated the technical 

note after the MCAI was issued. We are 

requiring you use the updated technical note 

(DG Flugzeugbau GmbH Technical Note No. 

301/26, Rev. 1, dated August 4, 2009) to do 

the actions of this AD, unless the AD 

specifies otherwise. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Greg Davison, Glider Program 

Manager, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4130; fax: (816) 

329–4090. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et.seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) Emergency AD No.: 

2009–0163–E, dated July 29, 2009, DG 

Flugzeugbau GmbH Technical Note No. 301/ 

26, dated July 16, 2009; DG Flugzeugbau 

GmbH Technical Note No. 301/26, Rev. 1, 

dated August 4, 2009; and DG Flugzeugbau 

Technical note No. 301/6, dated May 29, 

1978, for related information. 

Material Incorporated by Reference 

(i) You must use DG Flugzeugbau GmbH 

Technical Note No. 301/26, Rev. 1, dated 

August 4, 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 DG Flugzeugbau GmbH, 

Otto-Lilienthal-Weg 2, 76646 Bruchsal, 

Federal Republic of Germany; telephone: 

+ 49 (0) 7251 3020140; Fax: +49 (0) 7251 

3020149; Internet: http://www.dgflugzeugbau.de/index-e.html; E-Mail: 

dirks@dg-flugzeugbau.de. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on 

September 17, 2009. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E9–23047 Filed 9–28–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0431; Directorate 

Identifier 2007–NM–174–AD; Amendment 

39–16029; AD 2009–20–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–203 and –222 Airplanes and 

Model A300 B4–620 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing 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: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD 86–102–74(B) [which 

corresponds to FAA AD 88–06–03, 

amendment 39–5871] was issued to prevent 

development of damage, which was 

discovered during [a] fatigue test in the 

attachment angles of the rear pressure 

bulkhead (fuselage frame 80/82). 


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49806 Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations 

Following the life extension activities 

linked to the A310 program, the interval of 

inspection for A310–200 aircraft series was 

reduced from 12000 flight cycles (FC) to 9000 

FC * * *. 

Some stress analysis conducted in the 

frame of the life extension activities of the 

A300–600 program leads the manufacturer to 

reduce as well the interval of inspection 

applicable to A300B4–620 and A300C4–620 

aircraft models. 

* * * * * 

The unsafe condition is cracking in the 

attachment angles of the rear pressure 

bulkhead, which could result in failure 

of the rear pressure bulkhead. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

November 3, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 3, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1622; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on May 7, 2009 (74 FR 21274), 

and proposed to supersede AD 88–06– 

03, Amendment 39–5871 (53 FR 7730, 

March 10, 1988). That NPRM proposed 

to correct an unsafe condition for the 

specified products. The MCAI states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD 86–102–74(B) [which 

corresponds to FAA AD 88–06–03] was 

issued to prevent development of damage, 

which was discovered during [a] fatigue test 

in the attachment angles of the rear pressure 

bulkhead (fuselage frame 80/82). 

Following the life extension activities 

linked to the A310 program, the interval of 

inspection for A310–200 aircraft series was 

reduced from 12000 flight cycles (FC) to 9000 

FC, which prompted the issuance of EASA 

AD 2007–0157, superseding DGAC France 

AD 86–102–74(B). 

Some stress analysis conducted in the 

frame of the life extension activities of the 

A300–600 program leads the manufacturer to 

reduce as well the interval of inspection 

applicable to A300B4–620 and A300C4–620 

aircraft models. 

EASA AD 2007–0297 superseded EASA 

AD 2007–0157, retaining for A310 aircraft the 

requirements of EASA AD 2007–0157 and 

requiring the application of Airbus Service 

Bulletin (SB) A300–53–6005 Revision 4 on 

Airbus A300–600 aircraft, reducing the 

inspection interval from 12000 FC to 9000 

FC. 

[EASA] AD [2007–0297] has been revised 

to remove an inappropriate reference 

regarding the normal inspection program 

from the Compliance section, Note 3. 

The unsafe condition is cracking in the 

attachment angles of the rear pressure 

bulkhead, which could result in failure 

of the rear pressure bulkhead. The 

required actions include a modification 

of the rear pressure bulkhead to improve 

the fatigue life of the attachment angles 

at frame (FR) 80/82, and, for certain 

airplanes, repetitive inspections for 

cracks in the rear pressure bulkhead and 

repair if necessary. 

The modification includes installing 

additional attachment angles on the 

circumference of FR 80/82; installing a 

filler; installing additional supports 

between the aft pressure bulkhead and 

FR 80/82; installing an additional frame 

stiffener and support between the aft 

pressure bulkhead and FR 79 at stringer 

(STGR) 13; modifying the aft lavatories; 

applying surface protection to the 

modified area of the aft pressure 

bulkhead; modifying, reidentifying, and 

installing the heat and sound insulation 

in the area of STGR 9 and STGR 13 and 

between FR 79 and FR 80/82, left and 

right; and for certain airplanes, doing 

related investigative and corrective 

actions if necessary. 

The related investigative action is 

doing a visual inspection around the 

entire circumference between FR 80/82 

and the aft pressure bulkhead for 

damaged filler. The corrective action is 

removing any damaged filler and the 

adjacent area around the damage. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Revise Paragraph (f)(4) of 

the NPRM 

Airbus requests that we revise 

paragraph (f)(4) of the NPRM. Airbus 

states that for the airplanes identified in 

paragraph (f)(4) of the NPRM, it is not 

necessary to do the actions in 

accordance with the service bulletins 

specified in paragraph (f)(4) of the 

NPRM. Airbus further states that those 

airplanes are affected by Airworthiness 

Limitation Item (ALI) Task 531919–01– 

1A, as specified in the service bulletins 

identified in paragraph (f)(4) of this AD 

and the MCAI. 

We agree with the commenter. The 

actions specified in paragraph (f)(4) of 

the NPRM are not required for the 

airplanes identified in that paragraph 

because those airplanes are already 

inspected in accordance with ALI Task 

531919–01–1A, and no additional 

actions are necessary. We have 

confirmed with EASA that this is the 

intent of the MCAI. We have removed 

paragraph (f)(4) of the NPRM as it is 

unnecessary, and added a new Note 1 to 

this AD to clarify that no action is 

required by this AD for the airplanes 

discussed in this paragraph. We have reidentified the subsequent paragraphs 

accordingly. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 32 products of U.S. registry. We 

also estimate that it will take about 668 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $15,322 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these costs. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 


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Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations 49807 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$2,200,384, or $68,762 per product. 

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 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 this AD: 

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 AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 Amendment 39–5871 (53 FR 

7730, March 10, 1988) and adding the 

following new AD: 

2009–20–06 Airbus: Amendment 39–16029. 

Docket No. FAA–2009–0431; Directorate 

Identifier 2007–NM–174–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 3, 2009. 

Affected ADs 

(b) This AD supersedes AD 88–06–03, 

Amendment 39–5871. 

Applicability 

(c) This AD applies to Airbus Model A310– 

203 and –222 airplanes, and Model A300 B4– 

620 airplanes; certificated in any category; all 

serial numbers except airplanes on which 

Airbus Modification 05526 has been 

incorporated in production. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

DGAC (Direction Ge ́ne ́rale de l’Aviation 

Civile) France AD 86–102–74(B) [which 

corresponds to FAA AD 88–06–03, 

amendment 39–5871] was issued to prevent 

development of damage, which was 

discovered during [a] fatigue test in the 

attachment angles of the rear pressure 

bulkhead (fuselage frame 80/82). 

Following the life extension activities 

linked to the A310 program, the interval of 

inspection for A310–200 aircraft series was 

reduced from 12000 flight cycles (FC) to 9000 

FC, which prompted the issuance of EASA 

AD 2007–0157, superseding DGAC France 

AD 86–102–74(B). 

Some stress analysis conducted in the 

frame of the life extension activities of the 

A300–600 program leads the manufacturer to 

reduce as well the interval of inspection 

applicable to A300B4–620 and A300C4–620 

aircraft models. 

EASA AD 2007–0297 superseded EASA 

AD 2007–0157, retaining for A310 aircraft the 

requirements of EASA AD 2007–0157 and 

requiring the application of Airbus Service 

Bulletin (SB) A300–53–6005 Revision 4 on 

Airbus A300–600 aircraft, reducing the 

inspection interval from 12000 FC to 9000 

FC. 

[EASA] AD [2007–0297] has been revised 

to remove an inappropriate reference 

regarding the normal inspection program 

from the Compliance section, Note 3. 

The unsafe condition is cracking in the 

attachment angles of the rear pressure 

bulkhead, which could result in failure of the 

rear pressure bulkhead. The required actions 

include a modification of the rear pressure 

bulkhead to improve the fatigue life of the 

attachment angles at frame (FR) 80/82; 

applicable related investigative and 

corrective actions; and, for certain airplanes, 

repetitive inspections for cracks in the rear 

pressure bulkhead and repair if necessary. 

Requirements of This AD: Actions and 

Compliance 

(f) Unless already done, do the following 

actions. 

Modification 

(1) Except as required by paragraph (f)(2) 

of this AD: Before the accumulation of 12,000 

total flight cycles since first flight, or within 

1,500 flight cycles after the effective date of 

this AD, whichever occurs later, modify the 

aft pressure bulkhead to improve the fatigue 

life of the attachment angles at frame 80/82 

and do all applicable related investigative 

and corrective actions, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A300–53–6006, Revision 3, 

dated March 24, 1989; or Airbus Mandatory 

Service Bulletin A310–53–2025, Revision 06, 

dated August 3, 2006; as applicable. Do all 

applicable related investigative and 

corrective actions before further flight. 

(2) For airplanes identified in paragraph (c) 

of AD 2006–22–03, amendment 39–14800: At 

the earlier of the compliance times specified 

in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, 

do the actions specified in paragraph (f)(1) of 

this AD. 

(i) Before the accumulation of 12,000 total 

flight cycles since first flight, or within 1,500 

flight cycles after the effective date of this 

AD, whichever occurs later. 

(ii) At the compliance time specified in 

paragraph (h) of AD 2006–22–03. 

Inspections and Corrective Action 

(3) For airplanes on which the 

modification required by paragraph (f)(1) or 

(f)(2) of this AD is done after the 

accumulation of 6,000 total flight cycles 

since first flight: At the times specified in 

paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, 

do an eddy current inspection for any 

cracking in the critical area of the rear 

pressure bulkhead between stringers 8 and 

18, and repair all cracking before further 

flight, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–6005, 

Revision 04, dated July 18, 2007; or Airbus 

Mandatory Service Bulletin A310–53–2024, 

Revision 05, dated October 13, 2006; as 

applicable. 


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(i) Before or concurrently with the 

modification required by paragraph (f)(1) or 

(f)(2) of this AD, as applicable; and 

(ii) Before the accumulation of 18,000 total 

flight cycles since first flight, or within 1,500 

flight cycles after the effective date of this 

AD, whichever occurs later; and thereafter at 

intervals not to exceed 9,000 flight cycles. 

Note 1: For airplanes on which the 

modification required by paragraph (f)(1) or 

(f)(2) of this AD is done at or before the 

accumulation of 6,000 total flight cycles 

since first flight: No action is required by this 

AD. For these airplanes, refer to Airbus 

A300–600 ALI Task 531919–01–1A or Airbus 

A310 ALI Task 531919–01–1A, as applicable, 

for guidance on the normal inspection 

program. 

(4) Modifications done before the effective 

date of this AD in accordance with the 

service bulletins identified in Table 1 of this 

AD are acceptable for compliance with the 

requirements of paragraph (f)(1) and (f)(2) of 

this AD. 

TABLE 1—MODIFICATIONS DONE USING PREVIOUS SERVICE BULLETINS

Model— Airbus Service Bulletin— Revision— Dated— 

A300 B4–620 airplanes .................................... A300–53–6006 ................................................. Original ...................... May 6, 1986. 

A300–53–6006 ................................................. 1 ................................ September 19, 1986. 

A300–53–6006 ................................................. 2 ................................ August 11, 1988. 

A310–203 and –222 airplanes ......................... A310–53–2025 ................................................. Original ...................... April 21, 1986. 

A310–53–2025 ................................................. 1 ................................ September 19, 1986. 

A310–53–2025 ................................................. 2 ................................ February 16, 1987. 

A310–53–2025 ................................................. 3 ................................ April 7, 1987. 

A310–53–2025 ................................................. 4 ................................ October 20, 1987. 

A310–53–2025 ................................................. 5 ................................ March 24, 1989. 

(5) Inspections done before the effective 

date of this AD in accordance with the 

service bulletins identified in Table 2 of this 

AD are acceptable for compliance with the 

requirements of paragraph (f)(3) of this AD. 

TABLE 2—INSPECTIONS DONE WITH PREVIOUS SERVICE BULLETINS

Model— Airbus Service Bulletin— Revision— Dated— 

A300 B4–620 airplanes .................................... A300–53–6005 ................................................. Original ...................... May 6, 1986. 

A300–53–6005 ................................................. 1 ................................ June 20, 1986. 

A300–53–6005 ................................................. 2 ................................ September 22, 1986. 

A300–53–6005 ................................................. 3 ................................ April 22, 1987. 

A310–203 and –222 airplanes ......................... A310–53–2024 ................................................. Original ...................... April 21, 1986. 

A310–53–2024 ................................................. 1 ................................ June 20, 1986. 

A310–53–2024 ................................................. 2 ................................ October 2, 1986. 

A310–53–2024 ................................................. 3 ................................ February 17, 1987. 

A310–53–2024 ................................................. 4 ................................ February 2, 1988. 

(6) Modification of the aft pressure 

bulkhead to improve the fatigue life of the 

attachment angles at frame (FR) 80/82 in 

accordance with paragraph (h) of AD 2006– 

22–03 is acceptable for compliance with the 

corresponding requirement of paragraphs 

(f)(1) and (f)(2) of this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows. This 

AD includes a compliance time specified in 

paragraph (f)(2) of this AD for airplanes that 

are also affected by AD 2006–22–03. We 

realize that the requirements of this AD will 

necessitate that some operators do the 

modification required by paragraph (h) of AD 

2006–22–03 early. However, accomplishing 

the modification within the compliance time 

specified in this AD is required to address 

cracking in the attachment angles of the rear 

pressure bulkhead, which could result in 

failure of the rear pressure bulkhead. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Tom Stafford, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1622; fax (425) 227–1149. 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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI EASA Airworthiness 

Directive 2007–0297R1, dated September 17, 

2008, and the service bulletins listed in Table 

3 of this AD, for related information. 

TABLE 3—RELATED SERVICE BULLETINS

Airbus Service Bulletin Revision Date 

Airbus Mandatory Service Bulletin A300–53–6005 ..................................................................................... 04 July 18, 2007. 

Airbus Mandatory Service Bulletin A310–53–2024 ..................................................................................... 05 October 13, 2006. 

Airbus Mandatory Service Bulletin A310–53–2025 ..................................................................................... 06 August 3, 2006. 


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Federal Register / Vol. 74, No. 187 / Tuesday, September 29, 2009 / Rules and Regulations 49809 

TABLE 3—RELATED SERVICE BULLETINS—Continued 

Airbus Service Bulletin Revision Date 

Airbus Service Bulletin A300–53–6006 ....................................................................................................... 3 March 24, 1989. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 4 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 4—MATERIAL INCORPORATED BY REFERENCE

Airbus Service Bulletin Revision Date 

Airbus Mandatory Service Bulletin A300–53–6005 ..................................................................................... 04 July 18, 2007. 

Airbus Mandatory Service Bulletin A310–53–2024 ..................................................................................... 05 October 13, 2006. 

Airbus Mandatory Service Bulletin A310–53–2025 ..................................................................................... 06 August 3, 2006. 

Airbus Service Bulletin A300–53–6006 ....................................................................................................... 3 March 24, 1989. 

Airbus Service Bulletin A300–53–6006, 

Revision 3, dated March 24, 1989, contains 

the following effective pages: 

Page Nos. 

Revision level 

shown on 

page 

Date shown on page 

1, 29, 47, 48 ................................................................................................................................................ 3 March 24, 1989. 

2–28, 30–46, 49–52 ..................................................................................................................................... 2 August 11, 1988. 

(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 Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) 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. 

(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 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 

September 16, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–23094 Filed 9–28–09; 8:45 am] 

BILLING CODE 4910–13–P 

SUSQUEHANNA RIVER BASIN 

COMMISSION 

18 CFR Parts 806 and 808 

Review and Approval of Projects 

AGENCY: Susquehanna River Basin 

Commission. 

ACTION: Final rule. 

SUMMARY: This document contains 

amendments to the project review 

regulations of the Susquehanna River 

Basin Commission (Commission) 

including provisions restricting the use 

of docket reopening petitions to avoid 

abuses of process; amending the 

‘‘Approval by Rule’’ (ABR) process to 

allow for project sponsors to utilize 

approved water sources at approved 

drilling pad sites without the need for 

modification of the ABR; clarifying that 

the public hearing requirement for 

rulemaking shall be applicable to the 

proposed rulemaking stage of that 

process; and further providing for the 

time period within which 

administrative appeals must be filed. 

These amendments were first proposed 

in a Notice of Proposed Rulemaking 

(NOPR) that appeared at 74 FR 31647 on 

July 2, 2009. 

DATES: These rules are effective on 

November 1, 2009. 

ADDRESSES: Susquehanna River Basin 

Commission, 1721 N. Front Street, 

Harrisburg, PA 17102–2391. 

FOR FURTHER INFORMATION CONTACT: 

Richard A. Cairo, General Counsel, 

telephone: 717–238–0423, ext. 306; fax: 

717–238–2436; e-mail: rcairo@srbc.net. 

Also, for further information on the final 

rulemaking, visit the Commission’s Web 

site at http://www.srbc.net. 

SUPPLEMENTARY INFORMATION: 

Background and Purpose of 

Amendments 

The Commission convened public 

hearings on August 4, 2009, in 

Harrisburg, Pennsylvania and on August 

5, 2009, in Elmira, New York. A written 

comment period was held open until 

August 15, 2009. Comments were 

received at both the hearings and during 

the comment period. A summary of the 

comments and the Commission’s 

responses thereto follows. 

Comments by Section, Part 806 

Section 806.4 Projects Requiring 

Review and Approval 

Comment: The Commission’s 

proposal to require review and approval 

for any hydroelectric project regulated 

by the Federal Energy Regulatory 

Commission (FERC) and initiating a 

licensing or licensing amendment is 

defective and should not be adopted 

because: (1) As currently worded, the 


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