Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34585

temporary preventive action specified in

paragraph 2.E. of the Accomplishment

Instructions of the service bulletin allows the

repetitive inspections to be accomplished at

intervals of 600 flight hours until the

requirements of paragraph (b) of this AD have

been accomplished.

(2) If any discrepancy is found, prior to

further flight, accomplish the requirements of

either paragraph (a)(2)(i) or (a)(2)(ii) of this

AD in accordance with the service bulletin.

(i) Except as specified in paragraph (c),

accomplish the installation required by

paragraph (b) of this AD. Accomplishment of

this installation constitutes terminating

action for the requirements of this AD. Or

(ii) Accomplish the temporary preventive

action specified in paragraph 2.E. of the

Accomplishment Instructions of the service

bulletin. Thereafter, repeat the inspection

required by paragraph (a) of this AD at

intervals not to exceed 600 flight hours until

the requirements of paragraph (b) of this AD

have been accomplished.

(b) Except as specified in paragraph (c) of

this AD, within 3,000 flight hours after the

effective date of this AD, install the new

staked bushings in the aileron actuation

fitting in accordance with Saab Service

Bulletin 2000–57–014, Revision 02, dated

February 11, 1997. Accomplishment of this

installation terminates the requirements of

this AD.

(c) If, during the accomplishment of the

installation required by paragraph (a)(2)(i) or

paragraph (b) of this AD, the diameter of the

small hole of the fitting lug is found to be

outside the limits specified in Saab Service

Bulletin 2000–57–014, Revision 02, dated

February 11, 1997, prior to further flight,

repair it in accordance with a method

approved by either the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, or the

Luftfartsverket (or its delegated agent).

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

person shall install on any airplane an

aileron having part number, 7357995–843

(left-hand) or 7357995–844 (right-hand),

unless it has been modified in accordance

with paragraph (b) of this AD.

(e) 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(f) 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.

(g) Except as provided in paragraph (c) of

this AD, the actions shall be done in

accordance with Saab Service Bulletin 2000–

57–014, Revision 02, dated February 11,

1997. 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 SAAB Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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 Swedish airworthiness directive (SAD) No.

1–102R1, dated November 8, 1996.

(h) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 16,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16499 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–203–AD; Amendment

39–10626; AD 98–13–35]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9 and DC–9–80

Series Airplanes, Model MD–88

Airplanes, and C–9 (Military) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model DC–9 and DC–9–80

series airplanes, Model MD–88

airplanes, and C–9 (military) series

airplanes, that requires repetitive high

frequency eddy current inspections of

certain areas of the fuselage to detect

cracks of the skin and/or longeron, and

various follow-on actions. This

amendment also requires installation of

a preventative modification, which

terminates the repetitive inspections.

This amendment is prompted by reports

indicating that, due to material fatigue

caused by installation preload and cabin

pressurization cycles, fatigue cracks

were found in the skin and longerons of

the fuselage. The actions specified by

this AD are intended to prevent such

fatigue cracks, which could result in

loss of the structural integrity of the

fuselage and, consequently, lead to

rapid depressurization of the airplane.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from The Boeing Company, Douglas

Products Division, 3855 Lakewood

Boulevard, Long Beach, California

90846, Attention: Technical

Publications Business Administration,

Dept. C1–L51 (2–60). 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,

Transport Airplane Directorate, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Brent Bandley, Aerospace Engineer,

Airframe Branch, ANM–120L, FAA, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California 90712; telephone (562) 627–

5237; fax (562) 627–5210.

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 McDonnell

Douglas Model DC–9 and DC–9–80

series airplanes, Model MD–88

airplanes, and C–9 (military) series

airplanes was published in the Federal

Register on March 7, 1997 (62 FR

10492). That action proposed to require

repetitive high frequency eddy current

(HFEC) inspections of the external areas

of the fuselage skin to detect cracks of

the skin and/or longeron between

stations Y=160.000 and Y=218.000, and

various follow-on actions. That action

also proposed to require the installation

of a preventative modification, which

would constitute terminating action for

the repetitive inspection requirements.

Explanation of Changes Made to

Proposed AD

Since issuance of the NPRM, the FAA

has received a report indicating that,

during inspection of a McDonnell

Douglas Model DC–9–32 series airplane,

fatigue cracking was found in additional

structure that is within the subject area

of the proposed AD (i.e., between

stations Y=160.000 and Y=218.000). The

additional area is approximately 10

inches by 6 inches and is directly

between areas subject to the proposed

inspection required by this AD. Because
34586 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

of the small size of the additional area

and its location, the FAA finds that

adding this area to the existing

requirements of the final rule will not

increase significantly the inspection

burden on operators. Therefore, in

addition to the area between stations

Y=160.000 and Y=218.000 (as specified

in McDonnell Douglas DC–9 Service

Bulletin 53–235, which was referenced

in the proposed AD as the appropriate

source of service information), the FAA

has determined that the repetitive HFEC

inspections also must be conducted in

the entire area between stations

Y=160.000 and Y=180.000, longeron 4

left and longeron 5 left. The FAA has

revised paragraph (a) of the final rule

accordingly, and has added one work

hour to the cost impact information

below, to account for the additional

time necessary to accomplish the

required inspection. In addition,

McDonnell Douglas is planning on

revising the referenced service bulletin

to coincide with the requirements of

this final rule.

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.

Several commenters support the

proposed rule.

Request to Allow Credit for Inspections

Performed Previously

One commenter requests that the

compliance time for paragraph (a) of the

proposed AD be revised to allow credit

for internal visual inspections

performed previously in accordance

with Task C46–53300 of the Corrosion

Prevention and Control Program (CPCP)

[required by AD 92–22–08 R1,

amendment 39–8591 (58 FR 32281, June

9, 1993)]. The commenter states that,

since the primary failure mode is a

cracked longeron or shear clip, the

internal visual inspection will have a

crack detection threshold lower than

that of the initial external eddy current

inspection specified in paragraph (a) of

the proposed AD. The FAA concurs.

The FAA finds that the structure and

area specified in this AD are identical to

the structure and area being inspected

in accordance with the CPCP AD 92–

22–08 R1. The FAA has determined

that, for airplanes that have been

inspected previously in accordance with

Task C46–53300 of the CPCP (required

by AD 92–22–08 R1) within 6,000

landings prior to the effective date of

this AD, the initial HFEC inspection

required by this AD shall be

accomplished within 12,000 landings.

The FAA finds that a 12,000-landing

compliance time represents an

appropriate interval of time allowable

for these affected airplanes to continue

to operate without compromising safety.

The FAA has revised paragraph (a) of

the final rule accordingly.

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 changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 1,728

McDonnell Douglas Model DC–9 and

DC–9–80 series airplanes, Model MD–88

airplanes, and C–9 (military) series

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

1,152 airplanes of U.S. registry will be

affected by this AD.

It will take approximately 17 work

hours per airplane to accomplish the

required HFEC inspection, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

HFEC inspection required by this AD on

U.S. operators is estimated to be

$1,175,040, or $1,020 per airplane, per

inspection cycle.

It will take approximately 89 work

hours per airplane to accomplish the

required modification, at an average

labor rate of $60 per work hour. The

cost of required parts will range from

$13,771 to $15,292 per airplane. Based

on these figures, the cost impact of the

modification required by this AD on

U.S. operators is estimated to be

between $22,015,872 ($19,111 per

airplane) and $23,768,064 ($20,632 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

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:

98–13–35 McDonnell Douglas: Amendment

39–10626. Docket 96–NM–203–AD.

Applicability: Model DC–9–10, –20, –30,

–40, and –50 series airplanes; Model DC–9–

81 (MD–81), –82 (MD–82), –83 (MD–83), and

–87 (MD–87) series airplanes; Model MD–88

airplanes; and C–9 (military) series airplanes;

as listed in McDonnell Douglas DC–9 Service

Bulletin 53–235, dated September 15, 1993;

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 (f) 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.
Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34587

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue cracks in the skin and

longerons of the fuselage, which could result

in loss of the structural integrity of the

fuselage and, consequently, lead to rapid

depressurization of the airplane, accomplish

the following:

(a) Perform a high frequency eddy current

(HFEC) inspection of the external areas of the

fuselage to detect cracks of the skin and/or

longeron between stations Y=160.000 and

Y=218.000, in accordance with McDonnell

Douglas DC–9 Service Bulletin 53–235, dated

September 15, 1993; and of the entire area

between stations Y=160.000 and Y=180.000,

longeron 4 left and longeron 5 left. Perform

the inspection at the time specified in

paragraph (a)(1) or (a)(2) of this AD, as

applicable.

Note 2: Where there are differences

between this AD and the referenced service

bulletin, the AD prevails.

(1) For airplanes other than those

identified in paragraph (a)(2) of this AD:

Inspect prior to the accumulation of 30,000

total landings, or within 8,000 landings after

the effective date of this AD, whichever

occurs later.

(2) For airplanes that have been inspected

previously in accordance with Task C46–

53300 of the Corrosion Prevention and

Control Program (CPCP), as required by AD

92–22–8–R1, amendment 39–8591, within

6,000 flight cycles prior to the effective date

of this AD: Inspect within 12,000 landings

after the effective date of this AD.

(b) Condition 1 (No Cracks). If no crack is

detected during any inspection required by

this AD, accomplish either paragraph (b)(1)

or (b)(2) of this AD, in accordance with

McDonnell Douglas DC–9 Service Bulletin

53–235, dated September 15, 1993.

(1) Condition 1, Option I (Repetitive

Inspection). Repeat the HFEC inspection

required by paragraph (a) of this AD, and the

aided visual inspection specified in

paragraph 2.E. of the Accomplishment

Instructions of the service bulletin, at

intervals not to exceed 10,000 landings.

(2) Condition 1, Option II (Terminating

Action Modification). Accomplish the

preventative modification installation of

clips and doublers between stations

Y=160.000 and Y=218.000, in accordance

with the service bulletin. Accomplishment of

the modification constitutes terminating

action for the repetitive inspection

requirements of this AD.

(c) Condition 2 (Skin Cracks). If any skin

crack is detected during any inspection

required by this AD, prior to further flight,

repair it in accordance with McDonnell

Douglas DC–9 Service Bulletin 53–235, dated

September 15, 1993. After repair, accomplish

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

(d) Condition 3 (Longeron Cracks). If any

longeron crack is detected during any

inspection required by this AD, prior to

further flight, repair it in accordance with

McDonnell Douglas DC–9 Service Bulletin

53–235, dated September 15, 1993. After

repair, accomplish either paragraph (b)(1) or

(b)(2) of this AD.

(e) Prior to the accumulation of 100,000

total landings, or within 4 years after the

effective date of this AD, whichever occurs

later, accomplish the preventative

modification specified in paragraph 2.J. of

the Accomplishment Instructions of

McDonnell Douglas DC–9 Service Bulletin

53–235, dated September 15, 1993.

Accomplishment of the modification

constitutes terminating action for the

requirements of this AD.

(f) 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, Los

Angeles Aircraft Certification Office (ACO),

FAA, Transport Airplane Directorate.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Los Angeles ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(g) 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.

(h) The actions shall be done in accordance

with McDonnell Douglas DC–9 Service

Bulletin 53–235, dated September 15, 1993.

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 The Boeing Company, Douglas Products

Division, 3855 Lakewood Boulevard, Long

Beach, California 90846, Attention: Technical

Publications Business Administration, Dept.

C1–L51 (2–60). Copies may be inspected at

the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Transport

Airplane Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(i) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 17,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16695 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–212–AD; Amendment

39–10627; AD 98–13–36]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A, SAAB 340B, and SAAB

2000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

SF340A, SAAB 340B, and SAAB 2000

series airplanes, that requires repetitive

operational tests of the pitch trim

system of the elevator trim-tab of the

flight control unit to ensure that the

system operates correctly, and repair if

necessary. This amendment is prompted

by a report of uncommanded movement

of the right-hand elevator trim-tab to a

maximum deflection position, which

was apparently due to a failure in the

aircraft harness and a fault in the pitch

trim synchronizer. The actions specified

by this AD are intended to prevent such

uncommanded movement of the

elevator trim-tab, which could lead to

structural overload of the horizontal

stabilizers at speeds above 180 knots,

and consequent reduced controllability

of the airplane.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from SAAB Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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