5914 Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 

BAE Systems (Operations) Limited Alert 

Service Bulletin J41–A32–079, Revision 2. 

(3) Inspections and corrective actions 

accomplished before the effective date of this 

AD per BAE Systems (Operations) Limited 

Alert Service Bulletin J41–A32–079, Revision 

1, dated October 25, 2001, are acceptable for 

compliance with the corresponding actions 

required by this AD. 

(4) Although the alert service bulletin 

referenced in this AD specifies to submit 

certain information to the manufacturer, this 

AD does not include such a requirement. 

Inspections 

(b) Within 7 days after the effective date of 

this AD, do a detailed inspection for cracking 

of the NLG casing, per the alert service 

bulletin. Then, at the compliance time 

specified in paragraph (b)(1) or (b)(2) of this 

AD, as applicable, do a fluorescent dye 

penetrant inspection for cracking of the NLG 

casing, per the alert service bulletin. 

(1) If no cracking is found during the 

detailed inspection, within 30 days after 

accomplishment of the detailed inspection, 

do the fluorescent dye penetrant inspection. 

(2) If any cracking is found during the 

detailed inspection, before further flight, do 

the fluorescent dye penetrant inspection.

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 

(c) If any cracking is found during any 

inspection per paragraph (b) of this AD, 

before further flight, do paragraph (c)(1) or 

(c)(2) of this AD, as applicable, per the alert 

service bulletin. 

(1) If the cracking is within the limits 

specified in the alert service bulletin, repair 

the NLG casing. 

(2) If the cracking is outside the limits 

specified in the alert service bulletin, replace 

the NLG casing with a new or serviceable 

NLG casing.

Note 2: Although the alert service bulletin 

specifies that operators may contact the 

manufacturer for approval of a ferry flight to 

a location where the replacement of the NLG 

casing may be accomplished, this AD 

requires any ferry flight to be approved by 

the FAA, as specified in 14 CFR part 39.

Repetitive Inspections 

(d) Repeat the inspections in paragraph (b) 

of this AD, and the corrective action in 

paragraph (c) of this AD, as applicable, at 

intervals not to exceed 1,200 landings.

Note 3: There is no terminating action 

available at this time for the repetitive 

inspections required by paragraph (d) of this 

AD.

Parts Installation 

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

person may install an NLG casing on any 

airplane unless it has been inspected per 

paragraph (b) of this AD and found to be free 

of any cracking. 

Alternative Methods of Compliance 

(f) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(g) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

BAE Systems (Operations) Limited Alert 

Service Bulletin J41–A32–079, Revision 2, 

dated April 28, 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 British Aerospace Regional 

Aircraft American Support, 13850 Mclearen 

Road, Herndon, Virginia 20171. 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.

Note 4: The subject of this AD is addressed 

in British airworthiness directive 004–10–

2001.

Effective Date 

(h) This amendment becomes effective on 

March 15, 2004.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2463 Filed 2–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–376–AD; Amendment 

39–13456; AD 2004–03–12] 

RIN 2120–AA64 

Airworthiness Directives; Aerospatiale 

Model ATR72 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Aerospatiale Model 

ATR72 series airplanes, that currently 

requires initial and repetitive 

inspections to detect fatigue cracking in 

certain areas of the fuselage, and 

corrective actions if necessary. For 

certain airplanes, this amendment 

requires a new inspection for oversized 

fastener holes and cracking, and repair 

if necessary. The actions specified by 

this AD are intended to prevent fatigue 

cracking of the fuselage and the 

passenger and service doors, which 

could result in reduced structural 

integrity of the airplane. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective March 15, 2004. 

The incorporation by reference of a 

certain publication, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of March 15, 

2004. 

The incorporation by reference of 

certain other publications, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of April 3, 2000 (65 FR 

10381, February 28, 2000).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Aerospatiale, 316 Route de 

Bayonne, 31060 Toulouse, Cedex 03, 

France. 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:

Tony Jopling, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2190; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 2000–04–13, 

amendment 39–11596 (65 FR 10381, 

February 28, 2000), which is applicable 

to certain Aerospatiale Model ATR72 

series airplanes, was published in the 

Federal Register on November 28, 2003 

(68 FR 66772). The action proposed to 

continue to require initial and repetitive 

inspections to detect fatigue cracking in 

certain areas of the fuselage, and 

corrective actions if necessary. For 

certain airplanes, that action also 

proposed to require repair of oversized 

fastener holes. 

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. 

Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 5915

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 39 airplanes 

of U.S. registry that will be affected by 

this AD. 

The actions that are currently 

required by AD 2000–04–13 are as 

follows:

For airplanes identified in Avions de 

Transport Regional Service Bulletin 

ATR72–52–1018 (14 U.S.-registered 

airplanes), it takes approximately 250 

work hours per airplane to accomplish 

the required actions, at an average labor 

rate of $65 per work hour. Required 

parts will cost approximately $9,880 per 

airplane. Based on these figures, the cost 

impact of these actions required by this 

AD on U.S. operators is estimated to be 

$365,820, or $26,130 per airplane. 

For airplanes identified in Avions de 

Transport Regional Service Bulletin 

ATR72–53–1013, Revision 2 (2 U.S.-

registered airplanes), it will take 

approximately 3 work hours per 

airplane to accomplish the required 

actions, at an average labor rate of $65 

per work hour. Based on these figures, 

the cost impact of these actions required 

by this AD on U.S. operators is 

estimated to be $390, or $195 per 

airplane. 

For airplanes identified in Avions de 

Transport Regional Service Bulletin 

ATR72–53–1019, Revision 2 (2 U.S.-

registered airplanes), it will take 

approximately 100 work hours per 

airplane to accomplish the required 

actions, at an average labor rate of $65 

per work hour. Based on these figures, 

the cost impact of these actions required 

by this AD on U.S. operators is 

estimated to be $13,000, or $6,500 per 

airplane. 

For airplanes identified in Avions de 

Transport Regional Service Bulletin 

ATR72–52–1028 (2 U.S.-registered 

airplanes), it will take approximately 5 

work hours per airplane to accomplish 

the required actions, at an average labor 

rate of $65 per work hour. Based on 

these figures, the cost impact of these 

actions required by this AD on U.S. 

operators is estimated to be $650 or 

$325 per airplane, per inspection cycle. 

For airplanes identified in Avions de 

Transport Regional Service Bulletin 

ATR72–52–1033, and ATR72–52–1029, 

Revision 1 (2 U.S.-registered airplanes), 

it will take approximately 145 work 

hours per airplane to accomplish the 

required door stop fitting replacement, 

at an average labor rate of $65 per work 

hour. Required parts are provided by the 

manufacturer at no cost to the operators. 

Based on these figures, the cost impact 

of the stop fittings replacement required 

by this AD on U.S. operators is 

estimated to be $18,850 or $9,425 per 

airplane. 

For airplanes identified in Avions de 

Transport Regional Service Bulletin 

ATR72–53–1021, Revision 1 (2 U.S.-

registered airplanes) it will take 

approximately 30 work hours per 

airplane to accomplish the proposed 

actions, at an average labor rate of $65 

per work hour. Based on these figures, 

the cost impact of these actions required 

by this AD on U.S. operators is 

estimated to be $3,900, or $1,950 per 

airplane. 

For airplanes identified in Avions de 

Transport Regional Service Bulletin 

ATR72–53–1014, Revision 2 (2 U.S.-

registered airplanes), it will take 

approximately 8 work hours per 

airplane to accomplish the required 

actions, at an average labor rate of $65 

per work hour. Based on these figures, 

the cost impact of these actions required 

by this AD on U.S. operators is 

estimated to be $1,040, or $520 per 

airplane. 

For airplanes identified in Avions de 

Transport Regional Service Bulletin 

ATR72–53–1020 (14 U.S.-registered 

airplanes), it will take approximately 6 

work hours per airplane to accomplish 

the required actions, at an average labor 

rate of $65 per work hour. Based on 

these figures, the cost impact of these 

actions required by this AD on U.S. 

operators is estimated to be $5,460, or 

$390 per airplane. 

The new actions required by this AD 

are as follows: 

For airplanes identified in Avions de 

Transport Regional Service Bulletin 

ATR72–52–1018, Revision 1, 

accomplishment of the new actions, if 

required, will take approximately 250 

work hours per airplane to accomplish, 

at an average labor rate of $65 per work 

hour. Required parts will cost 

approximately $9,880 per airplane. 

Based on these figures, the cost impact 

of the new actions required by this AD 

on U.S. operators is estimated to be 

$26,130 per airplane. 

The cost impact figures discussed 

above are 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 

removing amendment 39–11596 (65 FR 

10381, February 28, 2000), and by adding 

a new airworthiness directive (AD), 

amendment 39–13456, to read as 

follows:

2004–03–12 Aerospatiale: Amendment 39–

13456. Docket 2001–NM–376–AD. 

Supersedes AD 2000–04–13, Amendment 

39–11596.

Applicability: Model ATR72 series 

airplanes; certificated in any category; listed 

in the following Avions de Transport 

Regional Service Bulletins: 

• ATR72–52–1018, dated May 18, 1995; 

• ATR72–52–1018, Revision 1, dated 

March 13, 2001; 

5916 Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 

• ATR72–52–1028, dated July 5, 1993; 

• ATR72–52–1029, Revision 1, dated 

November 16, 1994; 

• ATR72–52–1033, dated April 28, 1995; 

• ATR72–53–1013, Revision 2, dated 

March 22, 1993; 

• ATR72–53–1014, Revision 2, dated 

October 15, 1992; 

• ATR72–53–1019, Revision 2, dated 

October 15, 1996; 

• ATR72–53–1020, dated October 6, 1992; 

and 

• ATR72–53–1021, Revision 1, dated 

February 20, 1995. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent fatigue cracking of the fuselage 

and the passenger and service doors, which 

could result in reduced structural integrity of 

the airplane, accomplish the following: 

Restatement of Requirements of AD 2000–

04–13 

Inspections/Corrective Actions 

(a) For airplanes on which Aerospatiale 

Modification 03191 (reference Avions de 

Transport Regional Service Bulletin ATR72–

52–1018) has not been accomplished as of 

April 3, 2000 (the effective date of AD 2000–

04–13, amendment 39–11596); prior to the 

accumulation of 27,000 total flight cycles, or 

within 30 days after April 3, 2000: Perform 

a preliminary inspection of the existing 

fasteners to determine if the fasteners are out 

of tolerance in accordance with paragraph 

2.C.(1) of the Accomplishment Instructions of 

Avions de Transport Regional Service 

Bulletin ATR72–52–1018, dated May 18, 

1995. Depending on the results of the 

inspection, prior to further flight, accomplish 

the requirements in paragraphs (a)(1) and 

(a)(2), or (a)(2) and (a)(3) of this AD, as 

applicable. 

(1) Remove the fasteners and inspect the 

fastener holes to determine if they are out of 

tolerance or cracking, in accordance with 

Part A of the Accomplishment Instructions of 

the service bulletin. Perform a visual 

inspection of the holes for correct tolerance, 

and a high frequency eddy current (HFEC) 

inspection for cracking, in accordance with 

the service bulletin. 

(i) If any discrepancy is detected, prior to 

further flight, repair in accordance with Part 

C of the Accomplishment Instructions of the 

service bulletin. 

(ii) If no discrepancy is detected, prior to 

further flight, replace the cargo compartment 

door hinges with new hinges in accordance 

with Part A of the Accomplishment 

Instructions of the service bulletin. 

(2) Remove the existing fasteners and 

inspect the fastener holes for correct 

tolerance in accordance with Part B of the 

Accomplishment Instructions of the service 

bulletin. 

(i) If any discrepancy is detected, prior to 

further flight, repair in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate; or the Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC) (or its 

delegated agent). 

(ii) If no discrepancy is detected, prior to 

further flight, replace the cargo compartment 

door hinges with new hinges in accordance 

with Part B of the Accomplishment 

Instructions of the service bulletin. 

(3) Remove the existing fasteners, repair, 

and replace the cargo compartment door 

hinges with new hinges in accordance with 

Part C of the Accomplishment Instructions of 

the service bulletin. 

(b) For airplanes having serial numbers 108 

through 210 inclusive: Prior to the 

accumulation of 36,000 total flight cycles, or 

within 1 month after April 3, 2000, 

whichever occurs later, perform a one-time 

visual inspection to determine if rivets are 

installed in the key holes located on main 

frames 25 and 27 of the fuselage, between 

stringers 14 and 15, in accordance with 

Avions de Transport Regional Service 

Bulletin ATR72–53–1013, Revision 3, dated 

January 22, 1999. 

(1) If all rivets are installed, no further 

action is required by paragraph (b) of this 

AD. 

(2) If any rivet is missing, prior to further 

flight, perform an eddy current inspection of 

the affected key holes to detect cracks, in 

accordance with the service bulletin. 

(i) If no crack is detected during the 

inspection required by paragraph (b)(2) of 

this AD, prior to further flight, install rivets 

in all affected key holes, in accordance with 

the service bulletin. If installation of rivets is 

not possible, prior to further flight, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116; or 

the DGAC (or its delegated agent).

(ii) If any crack is detected during the 

inspection required by paragraph (b)(2) of 

this AD, prior to further flight, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116; or 

the DGAC (or its delegated agent). 

(c) For airplanes having serial numbers 108 

through 207 inclusive: Prior to the 

accumulation of 36,000 total flight cycles, or 

within 1 month after April 3, 2000, 

whichever occurs later, perform a one-time 

visual inspection to determine if rivets are 

installed in the tooling and key holes located 

on the standard frames of the fuselage, in 

accordance with Avions de Transport 

Regional Service Bulletin ATR72–53–1019, 

Revision 3, dated January 22, 1999. 

(1) If all rivets are installed, no further 

action is required by paragraph (c) of this AD. 

(2) If any rivet is missing, prior to further 

flight, perform a visual inspection of the 

affected tooling and key holes to detect 

cracks, in accordance with the service 

bulletin. 

(i) If no crack is detected during the 

inspection required by paragraph (c)(2) of 

this AD, prior to further flight, install new 

rivets in all affected tooling and key holes, 

in accordance with the service bulletin. 

(ii) If any crack is detected during the 

inspection required by paragraph (c)(2) of 

this AD, prior to further flight, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116; or 

the DGAC (or its delegated agent). 

(d) For airplanes on which Aerospatiale 

Modification 03775 (reference Avions de 

Transport Regional Service Bulletin ATR72–

52–1029, Revision 1, dated November 16, 

1994) or Aerospatiale Modification 03776 

(reference Avions de Transport Regional 

Service Bulletin ATR72–52–1033, dated 

April 28, 1995) has not been accomplished as 

of April 3, 2000: Prior to the accumulation 

of 12,000 total flight cycles, or within 1 

month after April 3, 2000, whichever occurs 

later, perform an eddy current inspection to 

detect cracks in the plug door stop fittings of 

the forward and aft passenger and service 

doors, in accordance with Avions de 

Transport Regional Service Bulletin ATR72–

52–1028, dated July 5, 1993. 

(1) If no crack is detected, repeat the eddy 

current inspection required by paragraph (d) 

of this AD thereafter at intervals not to 

exceed 6,000 flight cycles. 

(2) If any crack is detected, prior to further 

flight, replace the cracked stop fittings with 

new, improved fittings, in accordance with 

Avions de Transport Regional Service 

Bulletin ATR72–52–1033, dated April 28, 

1995; or ATR72–52–1029, Revision 1, dated 

November 16, 1994; as applicable. 

Accomplishment of the replacement 

constitutes terminating action for the 

repetitive inspection requirements of 

paragraph (d)(1) of this AD for that fitting. 

(e) For airplanes on which Aerospatiale 

Modification 03775 or Aerospatiale 

Modification 03776 has not been 

accomplished as of April 3, 2000: Prior to the 

accumulation of 18,000 total flight cycles, or 

within 1 month after April 3, 2000, 

whichever occurs later, replace the plug door 

stop fittings of the forward and aft passenger 

and service doors with new, improved 

fittings, in accordance with Avions de 

Transport Regional Service Bulletin ATR72–

52–1033, dated April 28, 1995; or ATR72–

52–1029, Revision 1, dated November 16, 

1994; as applicable. Accomplishment of the 

replacement constitutes terminating action 

for the repetitive inspection requirements of 

paragraph (d)(1) of this AD. 

(f) For airplanes on which Aerospatiale 

Modification 02986 (reference Avions de 

Transport Regional Service Bulletin ATR72–

53–1021, Revision 1, dated February 20, 

1995) has not been accomplished as of April 

3, 2000: Prior to the accumulation of 18,000 

total flight cycles, or within 1 month after 

April 3, 2000, whichever occurs later, 

perform a one-time eddy current inspection 

to detect cracks in the rivet holes of the door 

surround corners of the forward and aft 

passenger and service doors, in accordance 

with Avions de Transport Regional Service 

Bulletin ATR72–53–1021, Revision 1, dated 

February 20, 1995. 

(1) If no crack is detected during the 

inspection required by paragraph (f) of this 

AD, prior to further flight, modify the rivet 

holes, and replace the door surround corners 

with modified corners, in accordance with 

the service bulletin. 

(2) If any crack is detected during the 

inspection required by paragraph (f) of this 

AD, prior to further flight, repair and modify 

in accordance with a method approved by 

the Manager, International Branch, ANM–

116; or the DGAC (or its delegated agent). 

(g) For airplanes on which Aerospatiale 

Modification 02397 (reference Avions de 

Transport Regional Service Bulletin ATR72–

53–1014, Revision 2, dated October 15, 1992) 

has not been accomplished as of April 3, 

2000: Prior to the accumulation of 12,000 

Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 5917

total flight cycles, or within 1 month after 

April 3, 2000, whichever occurs later, 

perform a one-time eddy current inspection 

to detect cracks of the rivet holes located on 

the left and right sides of external stringer 4 

at frames 24 and 28 of the fuselage, in 

accordance with Avions de Transport 

Regional Service Bulletin ATR72–53–1014, 

Revision 2, dated October 15, 1992. 

(1) If no crack is detected during the 

inspection required by paragraph (g) of this 

AD, prior to further flight, install 

reinforcement angles on the left and right 

sides of external stringer 4 at frames 24 and 

28 of the fuselage, in accordance with the 

service bulletin. 

(2) If any crack is detected during the 

inspection required by paragraph (g) of this 

AD, prior to further flight, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116; or 

the DGAC (or its delegated agent). 

(h) For airplanes on which Aerospatiale 

Modification 03185 (reference Avions de 

Transport Regional Service Bulletin ATR72–

53–1020, dated October 6, 1992) has not been 

accomplished as of April 3, 2000: Prior to the 

accumulation of 12,000 total flight cycles, or 

within 1 month after April 3, 2000, 

whichever occurs later, perform a one-time 

eddy current inspection to detect cracks of 

the rivet holes located on stringer 11 of frame 

26 of the fuselage, in accordance with Avions 

de Transport Regional Service Bulletin 

ATR72–53–1020, dated October 6, 1992.

(1) If no crack is detected during the 

inspection required by paragraph (h) of this 

AD, prior to further flight, install doublers 

and stringer clips on the left and right sides 

on stringer 11 of frame 26 of the fuselage, in 

accordance with the service bulletin. 

(2) If any crack is detected during the 

inspection required by paragraph (h) of this 

AD, prior to further flight, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116; or 

the DGAC (or its delegated agent).

Note 1: Inspections and repairs 

accomplished prior to the effective date of 

this AD in accordance with Avions de 

Transport Regional Service Bulletins ATR72–

53–1013, dated June 10, 1991, or Revision 1, 

dated June 12, 1992; ATR72–53–1019, dated 

May 13, 1993, or Revision 1, dated November 

11, 1994; ATR72–52–1029, dated July 20, 

1994; or ATR72–53–1014, Revision 1, dated 

June 30, 1992; are considered acceptable for 

compliance with the applicable actions 

specified in this AD.

New Requirements of this AD 

Inspection/Repair 

(i) Prior to the accumulation of 27,000 total 

flight cycles, or within 30 days after the 

effective date of this AD, whichever is later; 

do the actions specified in paragraph (i)(1) or 

(i)(2) of this AD, as applicable. 

(1) For airplanes on which Aerospatiale 

Modification 3191 and Aerospatiale 

Modification 3184 have not been 

accomplished as of the effective date of this 

AD: No further action is required by 

paragraph (i) of this AD. 

(2) For airplanes on which Aerospatiale 

Modification 3191 has not been 

accomplished as of the effective date of this 

AD, and Aerospatiale Modification 3184 has 

been accomplished as of the effective date of 

this AD: Do a detailed inspection of the 

fastener holes at the hinge fitting of the cargo 

compartment doors to determine if the holes 

are oversized, and inspect the outer skin 

around the fastener holes for cracking, in 

accordance with the Accomplishment 

Instructions of Avions de Transport Regional 

Service Bulletin ATR72–52–1018, Revision 1, 

dated March 13, 2001.

Note 2: 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.’’

(j) Prior to further flight, repair any 

discrepancies detected during any inspection 

required by paragraph (i) of this AD in 

accordance with the Accomplishment 

Instructions of Avions de Transport Regional 

Service Bulletin ATR72–52–1018, Revision 1, 

dated March 13, 2001. Where the service 

bulletin specifies contacting the 

manufacturer for repair disposition, prior to 

further flight, repair in accordance with a 

method approved by the Manager, 

International Branch, ANM–116; or the 

DGAC (or its delegated agent). 

Alternative Methods of Compliance 

(k) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(l) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

the applicable Avions de Transport Regional 

Service Bulletins, as listed in Table 1 of this 

AD:

TABLE 1.—SERVICE BULLETINS

Service bulletin Revision level Date 

ATR72–52–1018 .................................................................... Original .................................................................................. May 18, 1995. 

ATR72–52–1018 .................................................................... Revision 1 ............................................................................. March 13, 2001. 

ATR72–52–1028 .................................................................... Original .................................................................................. July 5, 1993. 

ATR72–52–1029 .................................................................... Revision 1 ............................................................................. November 16, 1994. 

ATR72–52–1033 .................................................................... Original .................................................................................. April 28, 1995. 

ATR72–53–1013 .................................................................... Revision 3 ............................................................................. January 22, 1999. 

ATR72–53–1014 .................................................................... Revision 2 ............................................................................. October 15, 1992. 

ATR72–53–1019 .................................................................... Revision 3 ............................................................................. January 22, 1999. 

ATR72–53–1020 .................................................................... Original .................................................................................. October 6, 1992. 

ATR72–53–1021 .................................................................... Revision 1 ............................................................................. February 20, 1995. 

(1) The incorporation by reference of 

Avions de Transport Regional Service 

Bulletin ATR72–52–1018, Revision 1, dated 

March 13, 2001; is approved by the Director 

of the Federal Register in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) The incorporation by reference of the 

Avions de Transport Regional Service 

Bulletins listed in Table 2 of this AD was 

approved previously by the Director of the 

Federal Register as of April 3, 2000 (65 FR 

10381, February 28, 2000):

TABLE 2.—PREVIOUSLY APPROVED SERVICE BULLETINS

Service bulletin Revision level Date 

ATR72–52–1018 .................................................................... Original .................................................................................. May 18, 1995. 

ATR72–52–1028 .................................................................... Original .................................................................................. July 5, 1993. 

ATR72–52–1029 .................................................................... Revision 1 ............................................................................. November 16, 1994. 

ATR72–52–1033 .................................................................... Original .................................................................................. April 28, 1995. 

ATR72–53–1013 .................................................................... Revision 3 ............................................................................. January 22, 1999. 

ATR72–53–1014 .................................................................... Revision 2 ............................................................................. October 15, 1992. 

ATR72–53–1019 .................................................................... Revision 3 ............................................................................. January 22, 1999. 

5918 Federal Register / Vol. 69, No. 26 / Monday, February 9, 2004 / Rules and Regulations 

TABLE 2.—PREVIOUSLY APPROVED SERVICE BULLETINS—Continued

Service bulletin Revision level Date 

ATR72–53–1020 .................................................................... Original .................................................................................. October 6, 1992. 

ATR72–53–1021 .................................................................... Revision 1 ............................................................................. February 20, 1995. 

(3) Copies may be obtained from 

Aerospatiale, 316 Route de Bayonne, 31060 

Toulouse, Cedex 03, France. 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.

Note 3: The subject of this AD is addressed 

in French airworthiness directive 2001–142–

056(B), dated April 18, 2001.

Effective Date 

(m) This amendment becomes effective on 

March 15, 2004.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2586 Filed 2–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2001–NM–366–AD; Amendment 

39–13452; AD 2004–03–08] 

RIN 2120–AA64

Airworthiness Directives; Learjet 

Model 31, 31A, 35, 35A (C–21A), 36, 

and 36A Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Learjet Model 31, 

31A, 35, 35A (C–21A), 36, and 36A 

airplanes, that requires modification of 

the drag angles of the fuselage and 

engine pylons to gain access to the shear 

webs of the forward engine beams; 

repetitive inspections of the shear webs 

of the forward engine beams for cracks; 

follow-on actions; and modification/

repair of the shear webs of the forward 

engine beams, as necessary, which 

terminates the repetitive inspections. 

This action is necessary to prevent 

significant structural damage to the 

engine pylons, possible separation of 

the engines from the fuselage, and 

consequent reduced controllability of 

the airplane. This action is intended to 

address the identified unsafe condition.

DATES: Effective March 15, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of March 15, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Learjet, Inc., One Learjet Way, 

Wichita, Kansas 67209–2942. 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 FAA, 

Wichita Aircraft Certification Office, 

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or 

at the Office of the Federal Register, 800 

North Capitol Street, NW., suite 700, 

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Steven Litke, Aerospace Engineer, 

Airframe Branch, ACE–118W, FAA, 

Wichita Aircraft Certification Office, 

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 

67209; telephone (316) 946–4127; fax 

(316) 946–4107.

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 certain Learjet 

Model 31, 31A, 35, 35A (C–21A), 36, 

and 36A airplanes was published in the 

Federal Register on November 13, 2003 

(68 FR 64283). That action proposed to 

require modification of the drag angles 

of the fuselage and engine pylons to 

gain access to the shear webs of the 

forward engine beams; repetitive 

inspections of the shear webs of the 

forward engine beams for cracks; followon actions; and modification/repair of 

the shear webs of the forward engine 

beams, as necessary, which would 

terminate the repetitive inspections. 

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 

We have determined that air safety 

and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

There are approximately 893 

airplanes of the affected design in the 

worldwide fleet. We estimate that 673 

airplanes of U.S. registry will be affected 

by this AD. 

It will take between 2 and 3 work 

hours per airplane to accomplish the 

required modification, at an average 

labor rate of $65 per work hour. 

Required parts will cost approximately 

$243 per airplane. Based on these 

figures, the cost impact of the required 

modification on U.S. operators is 

estimated to be between $251,029 and 

$294,774, or between $373 and $438 per 

airplane. 

We estimate that it will take 3 work 

hours to perform the required 

inspections, and that the average labor 

rate is $65 per work hour. Based on this 

figure, the cost impact of the required 

inspections on U.S. operators is 

estimated to be $131,235, or $195 per 

airplane, per inspection cycle. 

The cost impact figures discussed 

above are 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. The 

manufacturer may cover the cost of 

replacement parts associated with this 

AD, subject to warranty conditions. 

Manufacturer warranty remedies may 

also be available for labor costs 

associated with this AD. As a result, the 

costs attributable to this AD may be less 

than stated above. 

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