23646 Federal Register / Vol. 69, No. 84 / Friday, April 30, 2004 / Rules and Regulations 

Inspection or Replacement and Corrective 

Actions 

(b) Within 18 months after the effective 

date of this AD, for both MLG, do the actions 

in either paragraph (b)(1) or (b)(2) of this AD. 

(1) Perform a gap measurement of the 

upper and lower joint gaps (includes 

measuring and recording upper and lower 

joint gaps twice); and an ultrasonic 

inspection of the outer cylinder of the main 

landing gear for cracks between the 

downlock fitting attach lugs, per Part 1 of the 

service bulletin. 

(2) Replace the outer cylinder of the main 

landing gear with a new or overhauled outer 

cylinder per Part 2 of the service bulletin. 

(c) If no crack is found during the 

inspection required by paragraph (b)(1) of 

this AD, before further flight, do the 

restoration (includes installing shims as 

applicable, electrical bracket, and cotter pins; 

and marking the main landing gear) per the 

service bulletin. 

(d) If any crack is found during the 

inspection required by paragraph (b)(1) of 

this AD: Before further flight, overhaul the 

outer cylinder of the MLG or replace the 

outer cylinder of the MLG with an 

interchangeable outer cylinder per Part 2 of 

the service bulletin, except as provided by 

paragraph (e) of this AD. 

(e) If any crack is found in the outer 

cylinder that cannot be removed within the 

repair limits specified in the service bulletin, 

during the overhaul specified in paragraph 

(d) of this AD, and the service bulletin 

specifies to contact Boeing for appropriate 

action: Before further flight, repair per a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA; or 

per data meeting the type certification basis 

of the airplane approved by a Boeing 

Company Designated Engineering 

Representative who has been authorized by 

the Manager, Seattle ACO, to make such 

findings. For a repair method to be approved, 

the approval must specifically reference this 

AD.

Note 1: When the outer cylinder is reinstalled, attach the downlock fittings onto 

the outer cylinder as specified in the 

applicable Boeing Component Maintenance 

Manual (CMM), Document Number 

161T1000, Section 32–11–19, Temporary 

Revision (TR) 32–61, dated March 26, 2002, 

or Section 32–11–19, pages 712 through 716, 

dated July 1, 2002, or dated July 1, 2003; or 

CMM Document Number 161T1000, Section 

32–11–20, TR 32–62, dated March 26, 2002, 

or Section 32–11–20, pages 718 through 722, 

dated July 1, 2002, or dated July 1, 2003.

Actions Accomplished Per Previous Issue of 

Service Bulletin 

(f) Accomplishment of the applicable 

actions before the effective date of this AD 

per Boeing Alert Service Bulletin 767–

32A0196, dated August 1, 2002; or Boeing 

Service Bulletin 767–32A0196, Revision 1, 

dated September 26, 2002; are considered 

acceptable for compliance with the 

corresponding action specified in this AD. 

Parts Installation 

(g) As of the effective date of this AD, no 

person may install a MLG on any airplane, 

unless the outer cylinder of the MLG has 

been inspected and follow-on and corrective 

actions have been accomplished per Boeing 

Service Bulletin 767–32A0196, Revision 2, 

dated May 15, 2003; or unless the outer 

cylinder is new; or unless the outer cylinder 

has not been installed on any airplane since 

its last overhaul. 

Alternative Methods of Compliance 

(h) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, FAA, is authorized to 

approve alternative methods of compliance 

for this AD. 

Incorporation by Reference 

(i) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing Service Bulletin 767–32A0196, 

Revision 2, dated May 15, 2003. This 

incorporation by reference was approved by 

the Director of the Federal Register in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Copies may be obtained from Boeing 

Commercial Airplanes, PO Box 3707, Seattle, 

Washington 98124–2207. Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the Federal 

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC. 

Effective Date 

(j) This amendment becomes effective on 

June 4, 2004.

Issued in Renton, Washington, on April 20, 

2004. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–9590 Filed 4–29–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–208–AD; Amendment 

39–13598; AD 2004–09–09] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–200C Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all Boeing Model 737–

200C series airplanes, that requires 

repetitive inspections of the Station 

348.2 frame to detect cracking under the 

stop fittings and intercostal flanges at 

Stringers 14L, 15L, and 16L; and 

corrective action if necessary. This 

action is necessary to prevent rapid 

decompression of the airplane, and 

possible separation of the forward entry 

door from the airplane. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective June 4, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of June 4, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, PO 

Box 3707, Seattle, Washington 98124–

2207. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the 

Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Howard Hall, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6430; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to all Boeing Model 

737–200C series airplanes was 

published in the Federal Register on 

February 19, 2004 (69 FR 7706). That 

action proposed to require repetitive 

inspections of the Station 348.2 frame to 

detect cracking under the stop fittings 

and intercostal flanges at Stringers 14L, 

15L, and 16L; and corrective action if 

necessary. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public. 

Conclusion 

The FAA has determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

There are approximately 78 airplanes 

of the affected design in the worldwide 

fleet. The FAA estimates that 15 

airplanes of U.S. registry will be affected 

by this AD, that it will take 

approximately 18 work hours per 

airplane to accomplish the required 

inspections, and that the average labor 

rate is $65 per work hour. Based on 

these figures, the cost impact of the AD 

on U.S. operators is estimated to be 

Federal Register / Vol. 69, No. 84 / Friday, April 30, 2004 / Rules and Regulations 23647

$17,550, or $1,170 per airplane, per 

inspection cycle. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–09–09 Boeing: Amendment 39–13598. 

Docket 2003–NM–208–AD.

Applicability: All Model 737–200C series 

airplanes; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent rapid decompression of the 

airplane, and possible separation of the 

forward entry door from the airplane, 

accomplish the following: 

Initial and Repetitive Inspections 

(a) Except as provided by paragraph (b) of 

this AD: Prior to the accumulation of 46,000 

total flight cycles, or within 2,250 flight 

cycles after the effective date of this AD, 

whichever occurs later, do detailed and eddy 

current inspections of the Station 348.2 frame 

for cracking under the stop fittings and 

intercostal flanges at Stringers 14L, 15L, and 

16L by accomplishing paragraphs 3.A. and 

3.B.1. through 3.B.7. of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1240, dated April 10, 2003. Do the 

actions per the service bulletin. Any 

applicable repair must be accomplished prior 

to further flight. Repeat the inspections 

thereafter at intervals not to exceed 4,500 

flight cycles.

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

Corrective Action 

(b) If any crack is found during any 

inspection required by this AD, and the 

bulletin specifies to contact Boeing for 

appropriate action: Before further flight, 

repair per a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA; or per data meeting the type 

certification basis of the airplane approved 

by a Boeing Company Designated 

Engineering Representative who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. For a repair method to 

be approved, the approval must specifically 

reference this AD. 

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, FAA, is authorized to 

approve alternative methods of compliance 

(AMOCs) for this AD. 

Incorporation by Reference 

(d) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing Alert Service Bulletin 737–53A1240, 

dated April 10, 2003. This incorporation by 

reference was approved by the Director of the 

Federal Register in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from Boeing Commercial Airplanes, 

PO Box 3707, Seattle, Washington 98124–

2207. Copies may be inspected at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, Washington, 

DC. 

Effective Date 

(e) This amendment becomes effective on 

June 4, 2004.

Issued in Renton, Washington, on April 20, 

2004. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–9591 Filed 4–29–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–341–AD; Amendment 

39–13599; AD 2004–09–10] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Boeing Model 747 

series airplanes. This AD requires a onetime inspection of the potable water and 

drain lines in the forward and aft cargo 

compartments for indications of 

overheating of the heater tape, exposed 

foam insulation, missing or damaged 

protective tape, or debris around the 

potable water fill and drain lines; and 

corrective action, if necessary. This 

action is necessary to prevent 

overheating of the heater tape on 

potable water fill and drain lines, which 

may ignite accumulated debris or 

contaminants on or near the potable 

water fill and drain lines, resulting in a 

fire in the airplane. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective June 4, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of June 4, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington