Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations 40819

(e) 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.

(f) The actions shall be done in accordance

with Dornier All Operators Telefax (AOT)

AOT–328–28–014, Revision 1, dated October

16, 1996; and Dornier Service Bulletin SB–

328–28–211, dated March 26, 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

FAIRCHILD DORNIER, DORNIER Luftfahrt

GmbH, P.O. Box 1103, D–82230 Wessling,

Germany. 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 German airworthiness directives 97–004,

dated January 30, 1997; and 97–149, dated

May 22, 1997.

(g) This amendment becomes effective on

September 4, 1998.

Issued in Renton, Washington, on July 24,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20433 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–44–AD; Amendment

39–10682; AD 98–16–06]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A310

series airplanes, that requires

inspections of the lower door

surrounding structure to detect cracks

and corrosion, and repair, if necessary.

This amendment also requires

inspections to detect cracking of the

holes of the corner doublers, the failsafe ring, and the door frames of the

door structures; and repair, if necessary.

In addition, this amendment provides

for optional terminating action for

certain inspections. This amendment is

prompted by reports indicating that

corrosion was found between the scuff

plates at exit and cargo doors, and

fatigue cracks originated from certain

fastener holes located in adjacent

structure. The actions specified by this

AD are intended to detect and correct

such corrosion and fatigue cracking,

which could result in reduced structural

integrity of the door surroundings.

DATES: Effective September 4, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

4, 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 all Airbus Model

A310 series airplanes was published in

the Federal Register on January 29,

1997 (62 FR 4208). That action proposed

to require inspections of the lower door

surrounding structure to detect cracks

and corrosion, and repair, if necessary.

That action also proposed to require

inspections to detect cracking of the

holes of the corner doublers, the failsafe ring, and the door frames of the

door structures; and repair, if necessary.

In addition, that action also provides for

optional terminating action for certain

inspections.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

Request to Mandate Optional

Terminating Action

One commenter supports the

proposed AD, but states that the FAA

should not allow operators to forego

accomplishment of the terminating

action in lieu of repetitive inspections.

The commenter states that allowing the

terminating action to be optional will

‘‘allow airplanes to operate that have

cracks in the door frames that will be

more subject to failure in the event of

an accident.’’ Additionally, the

commenter notes that accident history

has shown that there is already a

significant problem with the emergency

operation of doors following minor

fuselage deformation, even though this

is a requirement under section 25.783(c)

of the Federal Aviation Regulations [14

CFR 25.783(c)].

The FAA does not concur with the

request to mandate the terminating

action. As stated in the preamble to the

NPRM, the FAA considers certain

criteria in allowing repetitive

inspections of the affected area to be

permitted to continue, and has

determined that, in this case, mandating

the terminating action is not necessary

in order to adequately address the

identified unsafe condition. The FAA

has determined that the inspection

intervals required by the AD were

established to detect any cracking before

it becomes critical to the airplane

structure. Additionally, even if small

cracks exist that are not detected by the

inspections at the intervals required by

this AD, the cracks will not adversely

affect the structure of the door under

ultimate loads, and such cracking is

unlikely to result in interference with

the operation of emergency exits.

Therefore, no change to the final rule is

necessary.

Explanation of Change Made to This

Final Rule

Paragraphs (b), (c), and (d) of the final

rule have been revised to cite Revision

02 of Airbus Service Bulletin A310–53–

2041, dated July 2, 1996, for

accomplishment of certain actions.

Revision 02 contains no substantive

differences from Revision 1 of the

service bulletin (Revision 1 was cited as

the appropriate source of service

information in the proposed AD).

However, Revision 02 contains an

additional description of the inspections

required by paragraph (b) of the AD. A

‘‘NOTE’’ has been added to the final

rule to give credit to operators that may

have previously accomplished the

required actions in accordance with

Revision 1 of the service bulletin.

Conclusion

After careful review of the available

data, including the comment 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
40820 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 33 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 700

work hours per airplane to accomplish

the required inspections (including

access and close-up), and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the required inspections on U.S.

operators is estimated to be $1,386,000,

or $42,000 per airplane.

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.

Should an operator elect to

accomplish the optional terminating

action provided by this AD action, it

will take approximately 147 work hours

to accomplish it, at an average labor rate

of $60 per work hour. The cost of

required parts will be approximately

$5,581 per airplane. Based on these

figures, the cost impact of the optional

terminating action will be $14,401 per

airplane.

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:

98–16–06 Airbus Industrie: Amendment

39–10682. Docket 96–NM–44–AD.

Applicability: All Model A310 airplanes,

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 (i) 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 corrosion behind the

scuff plates at exit and cargo doors, and

fatigue cracking in certain fastener holes

located in adjacent structure, which could

result in reduced structural integrity of the

door surroundings, accomplish the following:

(a) Perform an initial inspection of the

areas behind the scuff plates below the

passenger/crew doors and bulk cargo door to

detect cracks and corrosion, in accordance

with Airbus Service Bulletin A310–53–2030,

Revision 5, dated March 6, 1991; at the

applicable time specified in paragraph (a)(1),

(a)(2), or (a)(3) of this AD. If any crack or

corrosion is found during this inspection,

prior to further flight, repair in accordance

with the service bulletin. Accomplishment of

this inspection is not required for the aft

passenger/crew doors if a steel doubler that

covers the entire inspection area is installed.

(1) For any door on which Modification

5382 has been accomplished: Perform the

initial inspection within 9 years since

airplane manufacture, or within 1 year after

the effective date of this AD, whichever

occurs later.

(2) For any door on which Modification

5382 has not been accomplished, and on

which the procedures described in Airbus

Service Bulletin A310–53–2004, Revision 2,

dated June 17, 1985, or Airbus Service

Information Letter 53–033, Revision 2, dated

November 23, 1984, have been accomplished:

Perform the initial inspection within 5 years

since airplane manufacture, or within 1 year

after the effective date of this AD, whichever

occurs later.

(3) For any door on which Modification

5382 has not been accomplished, and on

which the procedures described in Airbus

Service Bulletin A310–53–2004, Revision 2,

dated June 17, 1985, or Airbus Service

Information Letter 53–033, Revision 2, dated

November 23, 1984, have not been

accomplished: Perform the initial inspection

within 4 years since airplane manufacture, or

within 1 year after the effective date of this

AD, whichever occurs later.

(b) Perform repetitive inspections of the

areas behind the scuff plates below the

passenger/crew doors and bulk cargo door to

detect cracks and corrosion, in accordance

with Airbus Service Bulletin A310–53–2041,

Revision 02, dated July 2, 1996; at the

applicable times specified in paragraphs

(b)(1), (b)(2), and (b)(3) of this AD.

Accomplishment of these inspections is not

required for the aft passenger/crew doors if

a steel doubler that covers the entire

inspection area is installed.

(1) For the forward passenger/crew doors,

the bulk cargo door, and the aft passenger/

crew doors, except the upper and lower

edges of the fail-safe ring and the upper edges

of the corner doubler, on all Model A310–200

and –300 series airplanes: Perform the first

inspection within 5 years after accomplishing

the inspection required by paragraph (a) of

this AD; and repeat the inspection thereafter

at intervals not to exceed 5 years.

(2) For the upper and lower edges of the

fail-safe ring and the upper edges of the

corner doubler of the aft passenger/crew door

on all Model A310–200 series airplanes:

Perform the first inspection within 5 years or

12,000 landings after accomplishing the

inspection required by paragraph (a) of this

AD, whichever occurs first; and repeat the

inspection thereafter at intervals not to

exceed 5 years or 12,000 landings, whichever

occurs first.

(3) For the upper and lower edges of the

fail-safe ring and the upper edges of the

corner doubler of the aft passenger/crew door

on all Model A310–300 series airplanes:

Perform the first inspection within 5 years or

7,000 landings after accomplishing the

inspection required by paragraph (a) of this

AD, whichever occurs first; and repeat the

inspection thereafter at intervals not to

exceed 5 years or 7,000 landings, whichever

occurs first.

(c) If any crack is found during any

inspection required by paragraph (b) of this

AD, prior to further flight, repair in

accordance with Airbus Service Bulletin

A310–53–2041, Revision 02, dated July 2,

1996. Thereafter, perform the repetitive

inspections required by paragraph (b) of this

AD at the applicable times specified in

paragraphs (b)(1), (b)(2), and (b)(3) of this AD.

(d) If any corrosion is found during any

inspection required by paragraph (b) of this

AD, prior to further flight, repair in

accordance with Airbus Service Bulletin

A310–53–2041, Revision 02, dated July 2,

1996. Thereafter, perform the repetitive
Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations 40821

inspections required by paragraph (b) of this

AD at the applicable time specified in

paragraph (d)(1) or (d)(2) of this AD.

(1) For Model A310–200 series airplanes:

Inspect at intervals not to exceed 5 years or

9,600 landings, whichever occurs first.

(2) For Model A310–300 series airplanes:

Inspect at intervals not to exceed 5 years or

5,600 landings, whichever occurs first.

Note 2: Accomplishment of the actions

required by paragraph (b), (c), or (d) of this

AD in accordance with Airbus Service

Bulletin A310–53–2041, Revision 1, dated

March 6, 1991, prior to the effective date of

this AD, is acceptable for compliance with

that paragraph.

(e) Perform an inspection to detect cracking

of the holes of the corner doublers, the failsafe ring, and the door frames of the left-and

right-hand forward, mid, and aft passenger/

crew door structures, in accordance with

Airbus Service Bulletin A310–53–2037,

Revision 1, dated April 29, 1992, and at the

applicable times specified in paragraphs

(e)(1), (e)(2), and (e)(3) of this AD.

(1) For the upper corners of the forward

doors: Inspect prior to the accumulation of

20,000 total landings, or within 2,000

landings after the effective date of this AD,

whichever occurs later.

(2) For the lower corners of the forward

doors: Inspect prior to the accumulation of

20,000 total landings, or within 4,000

landings after the effective date of this AD,

whichever occurs later.

(3) For the upper and lower corners of the

aft doors, and for the parts underneath the

corners of the upper door frames: Inspect

prior to the accumulation of 20,000 total

landings, or within 4,000 landings after the

effective date of this AD, whichever occurs

later.

(f) Repeat the inspections required by

paragraph (e) of this AD at the applicable

times specified in paragraphs (f)(1), (f)(2),

(f)(3), (f)(4), and (f)(5).

(1) For the upper corners of the forward

doors: Inspect at intervals not to exceed 6,000

landings.

(2) For the lower corners of the forward

doors: Inspect at intervals not to exceed

10,000 landings.

(3) For the upper and lower corners of the

aft doors on which an inspection required by

paragraph (e) of this AD was accomplished

using a Roto test technique: Inspect at

intervals not to exceed 8,000 landings.

(4) For the upper and lower corners of the

aft doors on which an inspection required by

paragraph (e) of this AD was accomplished

using an X-ray technique: Inspect at intervals

not to exceed 3,500 landings.

(5) For the areas around the fasteners in the

vicinity of stringer 12 on the upper door

frames of the aft doors on which an

inspection required by paragraph (e) of this

AD was accomplished using a visual

technique: Inspect at intervals not to exceed

6,900 landings.

(g) If any crack is found during any

inspection required by paragraph (e) or (f) of

this AD: Prior to further flight, accomplish

the requirement of paragraph (g)(1) or (g)(2)

of this AD, as applicable.

(1) If any crack is found, and the crack can

be eliminated using the method specified in

Airbus Service Bulletin A310–53–2037,

Revision 1, dated April 29, 1992: Prior to

further flight, repair the crack in accordance

with that service bulletin.

(2) If any crack is found, and the crack

cannot be eliminated using the method

specified in Airbus Service Bulletin A310–

53–2037, Revision 1, dated April 29, 1992:

Prior to further flight, repair the crack in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate.

(h) Modification of the passenger/crew

door frames in accordance with Airbus

Service Bulletin A310–53–2017, Revision 7,

dated February 25, 1992, constitutes

terminating action for the repetitive

inspections required by paragraph (f) of this

AD.

(i) 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.

(j) Special flight permits may be issued in

accordance with §§ 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.

(k) Except as provided by paragraphs (g)(2)

and (h), the actions shall be done in

accordance with the following Airbus service

bulletins, which contain the specified

effective pages:

Service bulletin referenced and date Page number shown on page Revision level shown

on page Date shown on page

A310–53–2030, Revision 5, March 6, 1991 .............................. 1–2, 4–5, 7–9, 14 .................... 5 ................................ March 6, 1991.

3, 6, 10–13,15–17 ................... 4 ................................ December 5, 1990.

A310–53–2041, Revision 02, July 2, 1996 ................................ 1–21 ......................................... 02 .............................. July 2, 1996.

A300–53–2037, Revision 1, April 29, 1992 ............................... 1, 4, 6, 11–15, 18, 29, 39–44,

46, 57.

1 ................................ April 29, 1992.

2–3, 5, 7–10, 16–17, 19–28,

30–38, 45, 47–56, 58–60.

Original ...................... December 11, 1990.

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 91–132–

124(B), dated June 26, 1991, as amended by

a Correction, dated August 21, 1991.

(l) This amendment becomes effective on

September 4, 1998.

Issued in Renton, Washington, on July 24,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20338 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 98–ANM–05]

Establishment of Class E Airspace;

Moses Lake, WA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action establishes a Class

E surface area at Grant County Airport,

Moses Lake, WA. The effect of this

action is to provide controlled airspace

between the surface and the en route