Federal Register / Vol. 73, No. 99 / Wednesday, May 21, 2008 / Rules and Regulations 29421 

TABLE 1.—INITIAL INSPECTIONS—Continued 

AWL No. Description 

Compliance time 

(whichever occurs later) 

Threshold Grace period 

28–AWL–05 ............ A special detailed inspection of the 

bulkhead fitting bond for the hydraulic line tank penetration.

Within 72 months since the date of 

issuance of the original standard airworthiness certificate or the date of 

issuance of the original export certificate of airworthiness.

Within 60 months after the effective 

date of this AD. 

28–AWL–18 ............ A special detailed inspection of the 

lightning shield to ground termination 

on the out-of-tank fuel quantity indicating system to verify functional integrity.

Within 144 months since the date of 

issuance of the original standard airworthiness certificate or the date of 

issuance of the original export certificate of airworthiness.

Within 24 months after the effective 

date of this AD. 

28–AWL–26 ............ A special detailed inspection of the 

lightning shield to ground termination 

on the out-of-tank surge tank fuel 

level sensor to verify functional integrity.

Within 144 months since the date of 

issuance of the original standard airworthiness certificate or the date of 

issuance of the original export certificate of airworthiness.

Within 24 months after the effective 

date of this AD. 

No Alternative Inspections, Inspection 

Intervals, or Critical Design Configuration 

Control Limitations (CDCCLs) 

(i) After accomplishing the actions 

specified in paragraphs (g) and (h) of this AD, 

no alternative inspections, inspection 

intervals, or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are part of 

a later revision of Revision April 2008 of the 

MPD that is approved by the Manager, Seattle 

ACO; or unless the inspections, intervals, or 

CDCCLs are approved as an AMOC in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

Credit for Actions Done According to 

Previous Revisions of the MPD 

(j) Actions done before the effective date of 

this AD in accordance with Section 9 of the 

Boeing 767 Maintenance Planning Data 

(MPD) Document, D622T001–9, Revision 

March 2006; Revision October 2006; Revision 

January 2007; Revision October 2007; or 

Revision March 2008; are acceptable for 

compliance with the corresponding 

requirements of paragraphs (g) and (h) of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

Material Incorporated by Reference 

(l) You must use Section 9 of the Boeing 

767 Maintenance Planning Data (MPD) 

Document, D622T001–9, Revision April 

2008, 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, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or 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 May 8, 

2008. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–10976 Filed 5–20–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0024; Directorate 

Identifier 2007–NM–086–AD; Amendment 

39–15526; AD 2008–11–04] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Boeing Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

This AD requires repetitive inspections 

for cracking in and around the upper 

and lower hinge cutouts of the forward 

entry and forward galley service 

doorways, and corrective actions if 

necessary. This AD results from 

multiple reports of cracks found in the 

skin, bearstrap, and/or frame outer 

chord in the hinge cutout areas of the 

forward entry and forward galley service 

doorways. We are issuing this AD to 

detect and correct such cracking, which 

could result in rapid decompression of 

the airplane. 

DATES: This AD is effective June 25, 

2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 25, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Howard Hall, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 


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29422 Federal Register / Vol. 73, No. 99 / Wednesday, May 21, 2008 / Rules and Regulations 

Washington 98057–3356; telephone 

(425) 917–6430; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to all 

Boeing Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

That NPRM was published in the 

Federal Register on October 11, 2007 

(72 FR 57890). That NPRM proposed to 

require repetitive inspections for 

cracking in and around the upper and 

lower hinge cutouts of the forward entry 

and forward galley service doorways, 

and corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Add Optional Terminating 

Action for Certain Inspection Areas 

The Air Transport Association (ATA), 

on behalf of its member United Airlines, 

concurs with the contents of the NPRM. 

United adds that Boeing Alert Service 

Bulletin 737–53A1200, dated April 13, 

2006 (cited in the NPRM as the 

appropriate source of service 

information), does not require 

inspecting the hinge cutouts for cracks 

in the skin or bearstrap if an FAAapproved Boeing repair is installed. 

United requests that we revise the 

NPRM to include similar language. 

We partially agree. We agree that the 

inspections specified in paragraph (f) of 

this AD may be terminated at areas 

repaired in accordance with Boeing 

737–100/–200 SRM 53–30–3, Figures 

20, 21, 31, or 32; or Boeing 737–300/–

400/–500 SRM 53–10–01, Repair 5, 6, or 

8; as applicable. Boeing concurs with 

this provision. We have added the 

provision in new paragraph (i) of this 

AD, and re-identified subsequent 

paragraphs. But we do not agree that a 

nonspecified previously installed 

repair—even one issued by Boeing and 

approved by the FAA—is acceptable as 

a terminating action, unless the repair is 

properly evaluated as it relates to this 

AD. If a repair (or other modification or 

alteration) prevents an operator from 

accomplishing any action of this AD, 

then that operator must request FAA 

approval of an alternative method of 

compliance (AMOC) (14 CFR section 

39.17). Paragraph (j) of the final rule 

provides operators the opportunity to 

request approval of specific repair 

configurations as terminating action. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

There are about 2,437 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs, per inspection cycle, for 

U.S. operators to comply with this AD. 

ESTIMATED COSTS

Work hours 

Average 

hourly labor 

rate 

Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

13 to 14 ................................................ $80 $1,040 to $1,120 ......................... 1,055 $1,097,200 to $1,181,600. 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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 adding 

the following new AD: 

2008–11–04 Boeing: Amendment 39–15526. 

Docket No. FAA–2007–0024; Directorate 

Identifier 2007–NM–086–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective June 25, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

737–100, –200, –200C, –300, –400, and –500 

series airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from multiple reports 

of cracks found in the skin, bearstrap, and/ 

or frame outer chord in the hinge cutout 

areas of the forward entry and forward galley 

service doorways. We are issuing this AD to 

detect and correct such cracking, which 


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Federal Register / Vol. 73, No. 99 / Wednesday, May 21, 2008 / Rules and Regulations 29423 

could result in rapid decompression of the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Repetitive Inspections 

(f) Except as provided by paragraph (g) of 

this AD, at the applicable times specified in 

paragraph 1.E. of Boeing Alert Service 

Bulletin 737–53A1200, dated April 13, 2006, 

do external detailed, low frequency eddy 

current, high frequency eddy current, and 

high frequency eddy current rotary probe 

inspections, as applicable, for cracks in and 

around the upper and lower hinge cutouts of 

the forward entry and forward galley service 

doorways, in accordance with the 

Accomplishment Instructions of the service 

bulletin, except as provided by paragraphs 

(h) and (i) of this AD. Do not exceed the 

applicable repetitive interval for the previous 

inspection, as specified in the service 

bulletin as Option A or Option B. Repair any 

crack before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

Exceptions to Service Bulletin Specifications 

(g) Where Boeing Alert Service Bulletin 

737–53A1200, dated April 13, 2006, specifies 

a compliance time after the release date of 

the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(h) Although Boeing Alert Service Bulletin 

737–53A1200, dated April 13, 2006, specifies 

contacting Boeing for information about 

installing an optional preventive 

modification that would terminate the 

repetitive inspections specified in this AD, 

this AD requires that any terminating action 

be done by using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(i) The inspections specified in paragraph 

(f) of this AD may be terminated at areas 

repaired in accordance with Boeing 737–100/ 

–200 SRM 53–30–1, Figures 20, 21, 31, or 32; 

or Boeing 737–300/–400/–500 SRM 53–10–

01, Repair 5, 6, or 8; as applicable. 

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 in accordance with the procedures 

found in 14 CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

(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. 

Material Incorporated by Reference 

(k) You must use Boeing Alert Service 

Bulletin 737–53A1200, dated April 13, 2006, 

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, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or 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 May 9, 

2008. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–11118 Filed 5–20–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0048; Directorate 

Identifier 2007–NM–276–AD; Amendment 

39–15527; AD 2008–11–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 and A300–600 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

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: 

Based on some recent in-service findings 

for fluid ingress and/or inner skin disbond 

damage on rudders, AIRBUS decided to 

introduce some further structural inspections 

to specific rudder areas. This type of damage 

could result in reduced structural integrity of 

the rudder. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

25, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 25, 2008. 

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 January 22, 2008 (73 FR 

3656). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Based on some recent in-service findings 

for fluid ingress and/or inner skin disbond 

damage on rudders, AIRBUS decided to 

introduce some further structural inspections 

to specific rudder areas. This type of damage 

could result in reduced structural integrity of 

the rudder. 

For the reasons stated above, this AD 

requires the accomplishment of a thorough 

inspection program [a one-time inspection 

and repetitive inspections for damage of the 

rudder] by ultrasonic and/or t[h]ermographic 

methods, compared to the inspections 

already required by Airworthiness Directive 

(AD) 2006–0066, issued on 24 March 2006 

[which corresponds to FAA AD 2006–07–13] 

as a precautionary measure, in order to verify 

the structural integrity of the rudder. 

* * * * * 

The corrective actions include 

reporting both positive and negative 

findings to Airbus, doing a temporary 

repair, and contacting Airbus for repair 

instructions and doing a permanent 

repair. The compliance times for doing 

the repairs range from before further 

flight to within 4,500 flight cycles after 

doing the inspection, depending on the 

inspection type and the configuration of 


cprice-sewell on PROD1PC69 with RULES