Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 /Rules and Regulations 31345

The incorporation by reference of PW ASB

No. 6038, Revision 5, dated August 17, 1994,

was approved previously by the Director of

the Federal Register as of November 28, 1994

(59 FR 49175, September 27, 1994). Copies

may be obtained from Pratt & Whitney, 400

Main St., East Hartford, CT 06108; telephone

(860) 565–6600, fax (860) 565–4503. Copies

may be inspected at the FAA, New England

Region, Office of the Regional Counsel, 12

New England Executive Park, Burlington,

MA; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(m) This amendment becomes effective on

August 10, 1998.

Issued in Burlington, Massachusetts, on

May 29, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–15086 Filed 6–8–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–184–AD; Amendment

39–10573; AD 98–12–18]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320–111, –211, and –231 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320–111, –211, and –231 series

airplanes, that requires repetitive

inspections for cracking in the transition

and pick-up angles in the lower part of

the center fuselage area, and corrective

action, if necessary. This amendment

also provides for an optional

terminating modification for the

repetitive inspection requirements. This

amendment is prompted by the issuance

of mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

detect and correct fatigue cracking in

the transition and pick-up angles of the

lower part of the center fuselage, which

could result in reduced structural

integrity of the wing-fuselage support

and fuselage pressure vessel.

DATES: Effective July 14, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 14,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

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 Airbus

Model A320–111, –11, and –231 series

airplanes was published in the Federal

Register on November 19, 1997 (62 FR

61704). That action proposed to require

repetitive inspections for cracking in the

transition and pick-up angles in the

lower part of the center fuselage area,

and corrective action, if necessary. That

action also proposed to provide for an

optional terminating modification for

the repetitive inspection requirements.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Two commenters support the

proposed rule.

One commenter supports the intent of

the proposed rule, but identifies a

redundancy that appears in paragraph

(a)(2)(i)(A) of the proposed AD. The

commenter notes that the repetitive

inspection requirements of this

paragraph specify accomplishment of

both a visual and a rotating probe (eddy

current) inspection, whereas the original

requirement was only for an eddy

current inspection. Since the eddy

current inspection provides a greater

detailed inspection than a visual

inspection, the commenter states that

the visual inspection should not be

necessary. The FAA concurs and has

revised paragraph (a)(2)(i)(A) of the final

rule accordingly.

Additionally, paragraphs (a)(1)(i)(B),

(a)(1)(ii), and (a)(2)(i)(B) of the final rule

have been revised to cite only Revision

2 of Airbus Service Bulletin A320–53–

1027 for accomplishment of certain

actions. Revision 2 contains no

substantive differences from the original

or Revision 1 of the service bulletin. A

‘‘NOTE’’ has been added to the final

rule to give credit to operators who may

have previously accomplished the

required actions in accordance with

these earlier versions of the service

bulletin.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 24 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 9 work

hours per airplane to accomplish the

required inspections, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

inspections required by this AD on U.S.

operators is estimated to be $12,960, or

$540 per airplane, per inspection cycle.

It will take approximately 10 work

hours per airplane to accomplish the

required modification, at an average

labor rate of $60 per work hour.

Required parts will cost approximately

$2,895 per airplane. Based on these

figures, the cost impact of the

modification required by this AD on

U.S. operators is estimated to be

$83,880, or $3,495 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.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under
31346 Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 /Rules and Regulations

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:

98–12–18 Airbus Industrie: Amendment

39–10573. Docket 96–NM–184–AD.

Applicability: Model A320–111, –211, and

–231 series airplanes, manufacturer’s serial

numbers 002 through 008 inclusive, 010

through 014 inclusive, 016 through 078

inclusive, and 080 through 107 inclusive;

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (b) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct reduced structural

integrity of the wing-fuselage support and

fuselage pressure vessel resulting from

structural fatigue cracking in the transition

and pick-up angles, accomplish the

following:

(a) Prior to the accumulation of 16,000 total

landings, or within 6 months after the

effective date of this AD, whichever occurs

later, accomplish paragraphs (a)(1) and (a)(2)

of this AD, in accordance with Airbus

Service Bulletin A320–53–1028, dated March

1, 1994.

(1) Perform a visual inspection to detect

cracks of the transition angle, in accordance

with the service bulletin.

(i) If no crack is detected during the visual

inspection required by paragraph (a)(1) of

this AD, accomplish either paragraph

(a)(1)(i)(A) or paragraph (a)(1)(i)(B) of this

AD.

(A) Repeat the visual inspection thereafter

at intervals not to exceed 12,000 landings. Or

(B) Prior to further flight, modify the center

fuselage in accordance with Airbus Service

Bulletin A320–53–1027, Revision 2, dated

June 8, 1995. Accomplishment of the

modification constitutes terminating action

for the repetitive inspection requirements of

paragraph (a)(1)(i)(A) of this AD.

(ii) If any crack is detected during the

visual inspection required by paragraph (a)(1)

of this AD, prior to further flight, replace the

transition angle with a new transition angle,

in accordance with Airbus Service Bulletin

A320–53–1027, Revision 2, dated June 8,

1995.

(2) Perform a rotating probe inspection to

detect cracks of the pick-up angle, in

accordance with the service bulletin.

(i) If no crack is detected during the

rotating probe inspection required by

paragraph (a)(2) of this AD, accomplish either

paragraph (a)(2)(i)(A) or (a)(2)(i)(B) of this

AD.

(A) Repeat the rotating probe inspection

thereafter at intervals not to exceed 12,000

landings. Or

(B) Prior to further flight, modify the center

fuselage in accordance with Airbus Service

Bulletin A320–53–1027, Revision 2, dated

June 8, 1995. Accomplishment of the

modification constitutes terminating action

for the repetitive inspection requirements of

paragraph (a)(2)(i)(A) of this AD.

(ii) If any crack is detected and it is less

than 1.9 mm in length, prior to further flight,

accomplish the applicable corrective actions

specified in the service bulletin. For holes

that have not been modified in accordance

with the service bulletin, repeat the rotating

probe inspection thereafter at intervals not to

exceed 12,000 landings.

(iii) If any crack is detected and it is 1.9

mm or greater in length, prior to further

flight, repair it in accordance with the

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

Note 2: Accomplishment of the

modification or replacement required by

paragraph (a) of this AD in accordance with

Airbus Service Bulletin A320–53–1027,

dated March 1, 1994, or Revision 1, dated

September 5, 1994, prior to the effective date

of this AD, is acceptable for compliance with

this paragraph.

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(c) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(d) The inspections shall be done in

accordance with Airbus Service Bulletin

A320–53–1028, dated March 1, 1994. The

modification and replacement shall be done

in accordance with Airbus Service Bulletin

A320–53–1027, Revision 2, dated June 8,

1995. Airbus Service Bulletin A320–53–1027,

Revision 2, dated June 8, 1995, contains the

following list of effective pages:

Page No.

Revision

level

shown on

page

Date shown on

page

1–6, 8, 10–

16, 19.

2 ............. June 8, 1995.

7, 17, 18,

20.

Original .. March 1, 1994.

9 ................ 1 ............. September 5, 1994.

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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, 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 4: The subject of this AD is addressed

in French airworthiness directive 95–097–

065(B), dated May 24, 1995.

(e) This amendment becomes effective on

July 14, 1998.

Issued in Renton, Washington, on June 2,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15134 Filed 6–8–98; 8:45 am]

BILLING CODE 4910–13–P